title: Презентация на тему: MSC.Mvision Workshop 4

text:
$
$  MSC.Mvision v3 NASTRAN Material Data Export Utility
$  **   MSC.Mvision Evaluator is confidential & proprietary       **
$  **   to The MacNeal-Schwendler Corp. Use of this file is       **
$  **   limited to uses permitted by the MSC license agreement.   **
$
$  Materials record(s) generated by MSC.Mvision
$  Number of material records generated = 1
$  Materials data exported using template = MSC_NASTRAN_V68.Isotropic.Temperatu
$  re
$  Materials data exported from database = /mvision/release_3.0/db/ demo_metals.
$  des
$  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12-01
$   at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun Unix OS
$   4.1
$  Unit conversion = no conversion
$
$  Material Record 1 of 1
$   Databank Keys for record 1:
$     Databank Record Number = 7
$
$     User entered comments =
$
$
$     UNS= A97075
$     DESIG= QQ-A-250/25
$     FORM= Clad sheet
$     DIMS= T: 0.040-0.062 in
$     EXPOS= -0- h
$
$  Units and Footnotes for record 1:
$     Field            Units                    Footnote
$     -----            -----                    --------
$     FILENAME
$     MID
$     EvsTemp          Msi                      Primary value shown, Secondary
$  value:  9.8 Msi
$     NUvsTemp
$     RHO              lb/in^3
$     ALPHAvsTemp      micro-in/in-deg_F; deg_F
$     TREF             deg_F
$     GE
$     STvsTemp         ksi
$     SCvsTemp         ksi
$     SSvsTemp         ksi
$     MCSID
$     KvsTemp          BTU/hr-ft-deg_F; deg_F
$     CPvsTemp         BTU/lb-deg_F; deg_F
$
$  Data Source for record 1:
$     Field            Data Source              Expression
$     -----            -----------              ----------
$     FILENAME         *Modified By User*
$     MID              *Modified By User*
$     EvsTemp          Databank                 E11T
$     NUvsTemp         Databank                 NU12
$     RHO              Databank                 DENS
$     ALPHAvsTemp      Databank                 CTE11VSTEMP
$     TREF             Databank                 TEMP
$     GE               *No Data*
$     STvsTemp         Databank                 YS11T
$     SCvsTemp         Databank                 YS11C
$     SSvsTemp         Databank                 US12S
$     MCSID            *No Data*
$     KvsTemp          *No Data*                CTC11VSTEMP
$     CPvsTemp         Databank                 CPVSTEMP
$
$ This record will be written as an isotropic, temperature-dependent material.
$
$
$ For temperature dependent thermal expansion coefficients,
$ NASTRAN requires a curve of secant ALPHA vs. temperature.
$ This has been obtained from the database figure of
$ tangent ALPHA vs. temperature using TREF = 7.0000E+01
$
$ The following table shows the original data from the database
$ (first two columns), and the computed secant ALPHA.
$ An extra point on the table has been added at TREF = 7.0000E+01.
$
$      Stress Limit in Compression (ST) = 5.6000E+01
$      Stress Limit in Compression (SC) = 5.5000E+01
$      Stress Limit in Compression (SS) = 4.1000E+01
$ Material Coordinate System ID (MCSID) = 0
$
$
MAT1           1 10.3000         0.33000 0.10100 1.00000 70.0000     0.0+M     3
+M     3 56.0000 55.0000 41.0000       0
$
$
MATT1, 1, , , , , 1, , , +M4
+M4, , ,
$ The following TABLEM1 entry defines the temperature variation of CP:
$
TABLEM1        2                                                        +M     5
+M     5 29.5271 0.19944 185.946 0.21503 332.303 0.23131 590.739 0.25920+M     6
+M     6 798.112 0.28468 ENDT
$
$
$ The material properties written to the following MAT4 bulk data entry are:
$                     Material ID (MID) = 1
$              Thermal Conductivity (K) = 0.0000E+00
$                    Specific Heat (CP) = (TABLEM1 = 2)
$                         Density (RHO) = 1.0100E-01
$
$
MAT4           1     0.0 1.00000 0.10100
$
$
MATT4, 1, , 2
$
/COM
/COM  MSC.Mvision v3 ANSYS (Revision 5) Material Data Export Utility
/COM  **   MSC.Mvision Evaluator is confidential & proprietary       **
/COM  **   to The MacNeal-Schwendler Corp. Use of this file is       **
/COM  **   limited to uses permitted by the MSC license agreement.   **
/COM
/COM  Materials record(s) generated by MSC.Mvision
/COM  Number of material records generated = 1
/COM  Materials data exported using template = ANSYS_Release_5.Isotropic.Temper
/COM  ature
/COM  Materials data exported from database = /mvision/release_3.0/db/ demo_meta
/COM  ls.des
/COM  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12
/COM  -01 at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun U
/COM  nix OS 4.1
/COM  Unit conversion = no conversion
/COM
/COM  Material Record 1 of 1
/COM   Databank Keys for record 1:
/COM     Databank Record Number = 7
/COM
/COM     User entered comments =
/COM
/COM
/COM     UNS= A97075
/COM     DESIG= QQ-A-250/25
/COM     FORM= Clad sheet
/COM     DIMS= T: 0.040-0.062 in
/COM     EXPOS= -0- h
/COM
/COM  Units and Footnotes for record 1:
/COM     Field            Units                    Footnote
/COM     -----            -----                    --------
/COM     FILENAME
/COM     MID
/COM     EvsTemp          Msi                      Primary value shown, Seconda
/COM  ry value:  9.8 Msi
/COM     NUvsTemp
/COM     RHO              lb/in^3
/COM     ALPHAvsTemp      micro-in/in-deg_F; deg_F
/COM     TREF             deg_F
/COM     KvsTemp          BTU/hr-ft-deg_F; deg_F
/COM     CPvsTemp         BTU/lb-deg_F; deg_F
/COM
/COM  Data Source for record 1:
/COM     Field            Data Source              Expression
/COM     -----            -----------              ----------
/COM     FILENAME         *Modified By User*
/COM     MID              *Modified By User*
/COM     EvsTemp          Databank                 E11T
/COM     NUvsTemp         Databank                 NU12
/COM     RHO              Databank                 DENS
/COM     ALPHAvsTemp      Databank                 CTE11VSTEMP
/COM     TREF             Databank                 TEMP
/COM     KvsTemp          *No Data*                CTC11VSTEMP
/COM     CPvsTemp         Databank                 CPVSTEMP
/COM
/COM This record will be written as an isotropic, temperature-dependent material.
/COM
MP, EX,   2,  1.0300E+01
/COM
MP, PRXY, 2,  3.3000E-01
/COM
/COM
/COM For temperature dependent thermal expansion coefficients,
/COM ANSYS requires a curve of secant ALPX vs. temperature.
/COM This has been obtained from the database figure of
/COM tangent ALPX vs. temperature using TREF = 7.0000E+01
/COM
/COM The following table shows the original data from the database
/COM (first two columns), and the computed secant ALPX.
/COM An extra point on the table has been added at TREF = 7.0000E+01.
/COM
/COM          Temperature     Tangent ALPX    Secant ALPX
/COM          -----------    -------------   ------------
/COM           0.0000E+00       1.2081E+01     1.2207E+01
/COM   TREF =  7.0000E+01       1.2333E+01     1.2333E+01
/COM           2.3750E+02       1.2937E+01     1.2635E+01
/COM           3.0000E+02       1.3147E+01     1.2705E+01
/COM           4.4151E+02       1.3622E+01     1.2879E+01
/COM           6.2228E+02       1.4178E+01     1.3092E+01
/COM           7.9733E+02       1.4635E+01     1.3278E+01
/COM
/COM The following MPTEMP command gives the temperatures at which ALPX is defined:
/COM
MPTEMP,  1,  0.0000E+00,  7.0000E+01,  2.3750E+02,  3.0000E+02
MPTEMP,  5,  4.4151E+02,  6.2228E+02,  7.9733E+02
MPDATA, ALPX,  2,  1,  1.2207E+01,  1.2333E+01,  1.2635E+01,  1.2705E+01
MPDATA, ALPX,  2,  5,  1.2879E+01,  1.3092E+01,  1.3278E+01
MPTEMP
/COM
MP, REFT, 2,  7.0000E+01
/COM
MP, DENS, 2,  1.0100E-01
/COM
/COM The following MPTEMP command gives the temperatures at which C is defined:
/COM
MPTEMP,  1,  2.9527E+01,  1.8595E+02,  3.3230E+02,  5.9074E+02
MPTEMP,  5,  7.9811E+02
MPDATA, C,    2, 1,  1.9944E-01,  2.1503E-01,  2.3131E-01,  2.5920E-01
MPDATA, C,    2, 5,  2.8468E-01
MPTEMP
/COM
CLICK TO EDIT MASTER TITLE STYLE
MVI320, Workshop 4, August 2001
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Row 2
PLOT SET 1
Row 2
$
$  MSC.Mvision v3 NASTRAN Material Data Export Utility
$  **   MSC.Mvision Evaluator is confidential & proprietary       **
$  **   to The MacNeal-Schwendler Corp. Use of this file is       **
$  **   limited to uses permitted by the MSC license agreement.   **
$
$  Materials record(s) generated by MSC.Mvision
$  Number of material records generated = 1
$  Materials data exported using template = MSC_NASTRAN_V68.Isotropic.Temperatu
$  re
$  Materials data exported from database = /mvision/release_3.0/db/ demo_metals.
$  des
$  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12-01
$   at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun Unix OS
$   4.1
$  Unit conversion = no conversion
$
$  Material Record 1 of 1
$   Databank Keys for record 1:
$     Databank Record Number = 7
$
$     User entered comments =
$
$
$     UNS= A97075
$     DESIG= QQ-A-250/25
$     FORM= Clad sheet
$     DIMS= T: 0.040-0.062 in
$     EXPOS= -0- h
$
$  Units and Footnotes for record 1:
$     Field            Units                    Footnote
$     -----            -----                    --------
$     FILENAME
$     MID
$     EvsTemp          Msi                      Primary value shown, Secondary
$  value:  9.8 Msi
$     NUvsTemp
$     RHO              lb/in^3
$     ALPHAvsTemp      micro-in/in-deg_F; deg_F
$     TREF             deg_F
$     GE
$     STvsTemp         ksi
$     SCvsTemp         ksi
$     SSvsTemp         ksi
$     MCSID
$     KvsTemp          BTU/hr-ft-deg_F; deg_F
$     CPvsTemp         BTU/lb-deg_F; deg_F
$
$  Data Source for record 1:
$     Field            Data Source              Expression
$     -----            -----------              ----------
$     FILENAME         *Modified By User*
$     MID              *Modified By User*
$     EvsTemp          Databank                 E11T
$     NUvsTemp         Databank                 NU12
$     RHO              Databank                 DENS
$     ALPHAvsTemp      Databank                 CTE11VSTEMP
$     TREF             Databank                 TEMP
$     GE               *No Data*
$     STvsTemp         Databank                 YS11T
$     SCvsTemp         Databank                 YS11C
$     SSvsTemp         Databank                 US12S
$     MCSID            *No Data*
$     KvsTemp          *No Data*                CTC11VSTEMP
$     CPvsTemp         Databank                 CPVSTEMP
$
$ This record will be written as an isotropic, temperature-dependent material.
$
$
$ For temperature dependent thermal expansion coefficients,
$ NASTRAN requires a curve of secant ALPHA vs. temperature.
$ This has been obtained from the database figure of
$ tangent ALPHA vs. temperature using TREF = 7.0000E+01
$
$ The following table shows the original data from the database
$ (first two columns), and the computed secant ALPHA.
$ An extra point on the table has been added at TREF = 7.0000E+01.
$
$      Stress Limit in Compression (ST) = 5.6000E+01
$      Stress Limit in Compression (SC) = 5.5000E+01
$      Stress Limit in Compression (SS) = 4.1000E+01
$ Material Coordinate System ID (MCSID) = 0
$
$
MAT1           1 10.3000         0.33000 0.10100 1.00000 70.0000     0.0+M     3
+M     3 56.0000 55.0000 41.0000       0
$
$
MATT1, 1, , , , , 1, , , +M4
+M4, , ,
$ The following TABLEM1 entry defines the temperature variation of CP:
$
TABLEM1        2                                                        +M     5
+M     5 29.5271 0.19944 185.946 0.21503 332.303 0.23131 590.739 0.25920+M     6
+M     6 798.112 0.28468 ENDT
$
$
$ The material properties written to the following MAT4 bulk data entry are:
$                     Material ID (MID) = 1
$              Thermal Conductivity (K) = 0.0000E+00
$                    Specific Heat (CP) = (TABLEM1 = 2)
$                         Density (RHO) = 1.0100E-01
$
$
MAT4           1     0.0 1.00000 0.10100
$
$
MATT4, 1, , 2
$
/COM
/COM  MSC.Mvision v3 ANSYS (Revision 5) Material Data Export Utility
/COM  **   MSC.Mvision Evaluator is confidential & proprietary       **
/COM  **   to The MacNeal-Schwendler Corp. Use of this file is       **
/COM  **   limited to uses permitted by the MSC license agreement.   **
/COM
/COM  Materials record(s) generated by MSC.Mvision
/COM  Number of material records generated = 1
/COM  Materials data exported using template = ANSYS_Release_5.Isotropic.Temper
/COM  ature
/COM  Materials data exported from database = /mvision/release_3.0/db/ demo_meta
/COM  ls.des
/COM  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12
/COM  -01 at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun U
/COM  nix OS 4.1
/COM  Unit conversion = no conversion
/COM
/COM  Material Record 1 of 1
/COM   Databank Keys for record 1:
/COM     Databank Record Number = 7
/COM
/COM     User entered comments =
/COM
/COM
/COM     UNS= A97075
/COM     DESIG= QQ-A-250/25
/COM     FORM= Clad sheet
/COM     DIMS= T: 0.040-0.062 in
/COM     EXPOS= -0- h
/COM
/COM  Units and Footnotes for record 1:
/COM     Field            Units                    Footnote
/COM     -----            -----                    --------
/COM     FILENAME
/COM     MID
/COM     EvsTemp          Msi                      Primary value shown, Seconda
/COM  ry value:  9.8 Msi
/COM     NUvsTemp
/COM     RHO              lb/in^3
/COM     ALPHAvsTemp      micro-in/in-deg_F; deg_F
/COM     TREF             deg_F
/COM     KvsTemp          BTU/hr-ft-deg_F; deg_F
/COM     CPvsTemp         BTU/lb-deg_F; deg_F
/COM
/COM  Data Source for record 1:
/COM     Field            Data Source              Expression
/COM     -----            -----------              ----------
/COM     FILENAME         *Modified By User*
/COM     MID              *Modified By User*
/COM     EvsTemp          Databank                 E11T
/COM     NUvsTemp         Databank                 NU12
/COM     RHO              Databank                 DENS
/COM     ALPHAvsTemp      Databank                 CTE11VSTEMP
/COM     TREF             Databank                 TEMP
/COM     KvsTemp          *No Data*                CTC11VSTEMP
/COM     CPvsTemp         Databank                 CPVSTEMP
/COM
/COM This record will be written as an isotropic, temperature-dependent material.
/COM
MP, EX,   2,  1.0300E+01
/COM
MP, PRXY, 2,  3.3000E-01
/COM
/COM
/COM For temperature dependent thermal expansion coefficients,
/COM ANSYS requires a curve of secant ALPX vs. temperature.
/COM This has been obtained from the database figure of
/COM tangent ALPX vs. temperature using TREF = 7.0000E+01
/COM
/COM The following table shows the original data from the database
/COM (first two columns), and the computed secant ALPX.
/COM An extra point on the table has been added at TREF = 7.0000E+01.
/COM
/COM          Temperature     Tangent ALPX    Secant ALPX
/COM          -----------    -------------   ------------
/COM           0.0000E+00       1.2081E+01     1.2207E+01
/COM   TREF =  7.0000E+01       1.2333E+01     1.2333E+01
/COM           2.3750E+02       1.2937E+01     1.2635E+01
/COM           3.0000E+02       1.3147E+01     1.2705E+01
/COM           4.4151E+02       1.3622E+01     1.2879E+01
/COM           6.2228E+02       1.4178E+01     1.3092E+01
/COM           7.9733E+02       1.4635E+01     1.3278E+01
/COM
/COM The following MPTEMP command gives the temperatures at which ALPX is defined:
/COM
MPTEMP,  1,  0.0000E+00,  7.0000E+01,  2.3750E+02,  3.0000E+02
MPTEMP,  5,  4.4151E+02,  6.2228E+02,  7.9733E+02
MPDATA, ALPX,  2,  1,  1.2207E+01,  1.2333E+01,  1.2635E+01,  1.2705E+01
MPDATA, ALPX,  2,  5,  1.2879E+01,  1.3092E+01,  1.3278E+01
MPTEMP
/COM
MP, REFT, 2,  7.0000E+01
/COM
MP, DENS, 2,  1.0100E-01
/COM
/COM The following MPTEMP command gives the temperatures at which C is defined:
/COM
MPTEMP,  1,  2.9527E+01,  1.8595E+02,  3.3230E+02,  5.9074E+02
MPTEMP,  5,  7.9811E+02
MPDATA, C,    2, 1,  1.9944E-01,  2.1503E-01,  2.3131E-01,  2.5920E-01
MPDATA, C,    2, 5,  2.8468E-01
MPTEMP
/COM
$
$  MSC.Mvision v3 NASTRAN Material Data Export Utility
$  **   MSC.Mvision Evaluator is confidential & proprietary       **
$  **   to The MacNeal-Schwendler Corp. Use of this file is       **
$  **   limited to uses permitted by the MSC license agreement.   **
$
$  Materials record(s) generated by MSC.Mvision
$  Number of material records generated = 1
$  Materials data exported using template = MSC_NASTRAN_V68.Isotropic.Temperatu
$  re
$  Materials data exported from database = /mvision/release_3.0/db/ demo_metals.
$  des
$  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12-01
$   at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun Unix OS
$   4.1
$  Unit conversion = no conversion
$
$  Material Record 1 of 1
$   Databank Keys for record 1:
$     Databank Record Number = 7
$
$     User entered comments =
$
$
$     UNS= A97075
$     DESIG= QQ-A-250/25
$     FORM= Clad sheet
$     DIMS= T: 0.040-0.062 in
$     EXPOS= -0- h
$
$  Units and Footnotes for record 1:
$     Field            Units                    Footnote
$     -----            -----                    --------
$     FILENAME
$     MID
$     EvsTemp          Msi                      Primary value shown, Secondary
$  value:  9.8 Msi
$     NUvsTemp
$     RHO              lb/in^3
$     ALPHAvsTemp      micro-in/in-deg_F; deg_F
$     TREF             deg_F
$     GE
$     STvsTemp         ksi
$     SCvsTemp         ksi
$     SSvsTemp         ksi
$     MCSID
$     KvsTemp          BTU/hr-ft-deg_F; deg_F
$     CPvsTemp         BTU/lb-deg_F; deg_F
$
$  Data Source for record 1:
$     Field            Data Source              Expression
$     -----            -----------              ----------
$     FILENAME         *Modified By User*
$     MID              *Modified By User*
$     EvsTemp          Databank                 E11T
$     NUvsTemp         Databank                 NU12
$     RHO              Databank                 DENS
$     ALPHAvsTemp      Databank                 CTE11VSTEMP
$     TREF             Databank                 TEMP
$     GE               *No Data*
$     STvsTemp         Databank                 YS11T
$     SCvsTemp         Databank                 YS11C
$     SSvsTemp         Databank                 US12S
$     MCSID            *No Data*
$     KvsTemp          *No Data*                CTC11VSTEMP
$     CPvsTemp         Databank                 CPVSTEMP
$
$ This record will be written as an isotropic, temperature-dependent material.
$
$
$ For temperature dependent thermal expansion coefficients,
$ NASTRAN requires a curve of secant ALPHA vs. temperature.
$ This has been obtained from the database figure of
$ tangent ALPHA vs. temperature using TREF = 7.0000E+01
$
$ The following table shows the original data from the database
$ (first two columns), and the computed secant ALPHA.
$ An extra point on the table has been added at TREF = 7.0000E+01.
$
$      Stress Limit in Compression (ST) = 5.6000E+01
$      Stress Limit in Compression (SC) = 5.5000E+01
$      Stress Limit in Compression (SS) = 4.1000E+01
$ Material Coordinate System ID (MCSID) = 0
$
$
MAT1           1 10.3000         0.33000 0.10100 1.00000 70.0000     0.0+M     3
+M     3 56.0000 55.0000 41.0000       0
$
$
MATT1, 1, , , , , 1, , , +M4
+M4, , ,
$ The following TABLEM1 entry defines the temperature variation of CP:
$
TABLEM1        2                                                        +M     5
+M     5 29.5271 0.19944 185.946 0.21503 332.303 0.23131 590.739 0.25920+M     6
+M     6 798.112 0.28468 ENDT
$
$
$ The material properties written to the following MAT4 bulk data entry are:
$                     Material ID (MID) = 1
$              Thermal Conductivity (K) = 0.0000E+00
$                    Specific Heat (CP) = (TABLEM1 = 2)
$                         Density (RHO) = 1.0100E-01
$
$
MAT4           1     0.0 1.00000 0.10100
$
$
MATT4, 1, , 2
$
/COM
/COM  MSC.Mvision v3 ANSYS (Revision 5) Material Data Export Utility
/COM  **   MSC.Mvision Evaluator is confidential & proprietary       **
/COM  **   to The MacNeal-Schwendler Corp. Use of this file is       **
/COM  **   limited to uses permitted by the MSC license agreement.   **
/COM
/COM  Materials record(s) generated by MSC.Mvision
/COM  Number of material records generated = 1
/COM  Materials data exported using template = ANSYS_Release_5.Isotropic.Temper
/COM  ature
/COM  Materials data exported from database = /mvision/release_3.0/db/ demo_meta
/COM  ls.des
/COM  Additional database header info = M/VISION 2.0  Created by PDA on 1995-12
/COM  -01 at 15:49:53  Updated by PDA on 1995-12-01 at 15:49:53  System : Sun U
/COM  nix OS 4.1
/COM  Unit conversion = no conversion
/COM
/COM  Material Record 1 of 1
/COM   Databank Keys for record 1:
/COM     Databank Record Number = 7
/COM
/COM     User entered comments =
/COM
/COM
/COM     UNS= A97075
/COM     DESIG= QQ-A-250/25
/COM     FORM= Clad sheet
/COM     DIMS= T: 0.040-0.062 in
/COM     EXPOS= -0- h
/COM
/COM  Units and Footnotes for record 1:
/COM     Field            Units                    Footnote
/COM     -----            -----                    --------
/COM     FILENAME
/COM     MID
/COM     EvsTemp          Msi                      Primary value shown, Seconda
/COM  ry value:  9.8 Msi
/COM     NUvsTemp
/COM     RHO              lb/in^3
/COM     ALPHAvsTemp      micro-in/in-deg_F; deg_F
/COM     TREF             deg_F
/COM     KvsTemp          BTU/hr-ft-deg_F; deg_F
/COM     CPvsTemp         BTU/lb-deg_F; deg_F
/COM
/COM  Data Source for record 1:
/COM     Field            Data Source              Expression
/COM     -----            -----------              ----------
/COM     FILENAME         *Modified By User*
/COM     MID              *Modified By User*
/COM     EvsTemp          Databank                 E11T
/COM     NUvsTemp         Databank                 NU12
/COM     RHO              Databank                 DENS
/COM     ALPHAvsTemp      Databank                 CTE11VSTEMP
/COM     TREF             Databank                 TEMP
/COM     KvsTemp          *No Data*                CTC11VSTEMP
/COM     CPvsTemp         Databank                 CPVSTEMP
/COM
/COM This record will be written as an isotropic, temperature-dependent material.
/COM
MP, EX,   2,  1.0300E+01
/COM
MP, PRXY, 2,  3.3000E-01
/COM
/COM
/COM For temperature dependent thermal expansion coefficients,
/COM ANSYS requires a curve of secant ALPX vs. temperature.
/COM This has been obtained from the database figure of
/COM tangent ALPX vs. temperature using TREF = 7.0000E+01
/COM
/COM The following table shows the original data from the database
/COM (first two columns), and the computed secant ALPX.
/COM An extra point on the table has been added at TREF = 7.0000E+01.
/COM
/COM          Temperature     Tangent ALPX    Secant ALPX
/COM          -----------    -------------   ------------
/COM           0.0000E+00       1.2081E+01     1.2207E+01
/COM   TREF =  7.0000E+01       1.2333E+01     1.2333E+01
/COM           2.3750E+02       1.2937E+01     1.2635E+01
/COM           3.0000E+02       1.3147E+01     1.2705E+01
/COM           4.4151E+02       1.3622E+01     1.2879E+01
/COM           6.2228E+02       1.4178E+01     1.3092E+01
/COM           7.9733E+02       1.4635E+01     1.3278E+01
/COM
/COM The following MPTEMP command gives the temperatures at which ALPX is defined:
/COM
MPTEMP,  1,  0.0000E+00,  7.0000E+01,  2.3750E+02,  3.0000E+02
MPTEMP,  5,  4.4151E+02,  6.2228E+02,  7.9733E+02
MPDATA, ALPX,  2,  1,  1.2207E+01,  1.2333E+01,  1.2635E+01,  1.2705E+01
MPDATA, ALPX,  2,  5,  1.2879E+01,  1.3092E+01,  1.3278E+01
MPTEMP
/COM
MP, REFT, 2,  7.0000E+01
/COM
MP, DENS, 2,  1.0100E-01
/COM
/COM The following MPTEMP command gives the temperatures at which C is defined:
/COM
MPTEMP,  1,  2.9527E+01,  1.8595E+02,  3.3230E+02,  5.9074E+02
MPTEMP,  5,  7.9811E+02
MPDATA, C,    2, 1,  1.9944E-01,  2.1503E-01,  2.3131E-01,  2.5920E-01
MPDATA, C,    2, 5,  2.8468E-01
MPTEMP
/COM


title: Презентация на тему: MSC.Flightloads 5.5

text:
Geometry Manipulation: Surface Breaking
Geometry Manipulation: Breaking Remaining Surfaces
Aerodynamic Mesh Divisions
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Click to edit Master title style
FLDS120 Section 5.5, June 2002
Click to edit Master text styles
Second level
Third level
Fourth level
Fifth level
Click to edit Master text styles
Second level
Third level
Fourth level
Fifth level
Original Curve
Point to extend from
New Curve
Curve  1
Surface  1
The single canard surface is now split into two
A query box asks if you wish to delete the original surface, yes in this case
The same procedure is now repeated until we have a set of conforming geometry boxes on the canard
The aero meshing strategy is shown here in terms of number of spanwise and chordwise aeor elements for each surface
Biasing could be used where steeper pressure gradients are anticipated
This will be used as an exercise for the student later
10 constant
3 constant
3 constant
5 constant
3 constant
3 constant
7 constant
This division ignored
3 constant
Aero Mesh
Fuselage centre
Aero Mesh
Inboard Wing
N O N - D I M E N S I O N A L   S T A B I L I T Y   A N D   C O N T R O L   D E R I V A T I V E
   C O E F F I C I E N T S

        CONFIGURATION = TS1          XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                          MACH = 5.0000E-01                    Q = 2.5718E+00
                         CHORD = 9.5000E+01           SPAN = 3.1920E+02            AREA = 1.9829E+04

First Trim condition: M = 0.5, q = 2.5718 psi, equates to Sea Level, 330 Kts     (6697 in/s)
Basic Lift Curve slope due to angle of attack
Canard term
Pitch Rate term
Ignored term
Zero term
Pitch Accn. term
Vert Accn. term
 CONTROLLER STATE: INTERCEPT ONLY, ALL CONTROLLERS ARE ZERO

    TRIM VARIABLE   COEFFICIENT              RIGID                         ELASTIC                          INERTIAL
                                   UNSPLINED        SPLINED       RESTRAINED      UNRESTRAINED     RESTRAINED      UNRESTRAINED

    REF. COEFF.      CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.061313E-19    2.253668E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ        -2.192298E-14   -2.192298E-14    -2.352667E-14   -2.399215E-14    -1.279110E-17   -2.399215E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        2.565092E-14    2.565092E-14     2.801416E-14    2.837849E-14     3.980359E-17    2.836162E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    CANARD           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.858715E-19    1.349451E-02
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         2.358309E-01    2.358309E-01     2.103891E-01    1.993592E-01    -3.859970E-18    1.993592E-01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        4.983479E-01    4.983479E-01     5.322815E-01    5.458433E-01     1.216183E-17    5.448329E-01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    ANGLEA           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.195443E-20   -5.296896E-03
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         3.400623E+00    3.400623E+00     3.665259E+00    3.713126E+00    -1.157451E-18    3.713126E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -2.474000E+00   -2.474000E+00    -2.859308E+00   -2.887297E+00     3.962711E-18   -2.886900E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    SIDES            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
.....
z
C
0

    ROLL             CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    PITCH            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.239254E-19   -1.409231E-01
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.121193E+01    1.121193E+01     1.205719E+01    1.231879E+01    -2.514021E-18    1.231879E+01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.439519E+01   -1.439519E+01    -1.564026E+01   -1.585319E+01     8.066646E-18   -1.584263E+01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    YAW              CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD1            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -4.625457E-19   -1.282328E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.119897E-14    1.119897E-14     1.202170E-14    1.227077E-14     9.899729E-18    1.227077E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.376156E-14   -1.376156E-14    -1.497476E-14   -1.517384E-14    -3.047236E-17   -1.516424E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD2            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD3            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -1.067984E-18   -1.301176E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.187761E-14    1.187761E-14    -8.996639E-08    1.300619E-14     3.634104E-04    1.300619E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.430087E-14   -1.430087E-14     1.153184E-06   -1.578820E-14    -2.562158E-04   -1.577846E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
 Roll Term n/a
 x accn term n/a
 y accn term n/a
 Yaw Term n/a

    URDD4            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD5            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.116072E-03   -1.284997E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.155316E-14    1.155316E-14    -6.621490E-04    1.265632E-14    -2.434050E-02    1.265632E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.400548E-14   -1.400548E-14     8.048715E-04   -1.545924E-14     7.384621E-02   -1.544961E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD6            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
 yaw accn term n/a
 roll accn term n/a

     TRIM ALGORITHM USED: LINEAR TRIM SOLUTION WITHOUT REDUNDANT CONTROL SURFACES.

                                                      AEROELASTIC TRIM VARIABLES

                                  ID     LABEL                 TYPE        TRIM STATUS      VALUE OF UX

                                         INTERCEPT          RIGID BODY           FIXED      1.000000E+00
                                   1     CANARD        CONTROL SURFACE            FREE      1.452887E-02  RADIANS
                                   2     ANGLEA             RIGID BODY            FREE      3.746328E-02  RADIANS
                                   3     SIDES              RIGID BODY           FIXED      0.000000E+00  RADIANS
                                   4     ROLL               RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   5     PITCH              RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   6     YAW                RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   7     URDD1              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                   8     URDD2              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                   9     URDD3              RIGID BODY           FIXED      3.861600E+02  LENGTH/S/S
                                  10     URDD4              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                  11     URDD5              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                  12     URDD6              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S

      AERODYNAMIC MONITOR POINT TOTAL VEHICLE COEFFICIENTS:
          AXIS         RIGID AIR

    BODY  CZ          1.308248E-01
    WIND  CL          1.307330E-01

                                           CONTROL SURFACE POSITION AND HINGE MOMENT RESULTS

                            ACTIVE LIMITS ARE FLAGGED WITH AN (A),  VIOLATED LIMITS ARE FLAGGED WITH A (V).

                                                POSITION                                         HINGE MOMENT
          CONTROL SURFACE      LOWER LIMIT       VALUE         UPPER LIMIT        LOWER LIMIT       VALUE         UPPER LIMIT
              CANARD         -9.000020E+01    1.452887E-02    9.000021E+01            N/A        9.530430E+03         N/A

 INTERMEDIATE MATRIX ... HP

                                                            COLUMN      1
     1                                              -7.441844E-14       2.471184E-16                                              2

                                                            COLUMN      2
     1                                              -5.960365E-01       1.967810E-03                                              2

                                                            COLUMN      3
     1                                               9.598665E+00      -3.165875E-02                                              2

                                                            COLUMN      6
     1                                               3.998297E+01      -1.328564E-01                                              2

                                                            COLUMN      8
     1                                               3.895659E-14      -1.294318E-16                                              2

                                                            COLUMN     10
     1                                               5.399570E-04      -1.834221E-06                                              2

                                                            COLUMN     12
     1                                              -8.921152E-02       3.054205E-04                                              2

 S T R U C T U R A L   M O N I T O R   P O I N T   I N T E G R A T E D   L O A D S
                         CONFIGURATION = AEROSG2D     XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                           MACH = 5.000000E-01                Q = 2.571800E+00

        CONTROLLER STATE:
        CANARD   =   1.4529E-02        ANGLEA   =   3.7463E-02        URDD3    =   3.8616E+02

         MONITOR POINT NAME = AEROSG2D          COMPONENT =                   CLASS = COEFFICIENT
        LABEL = Full Vehicle Integrated Loads
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.      INERTIAL      RIGID APPLIED    REST. APPLIED
          ----    -------------    -------------    -------------    -------------    -------------
           CX     0.000000E+00     0.000000E+00    -1.276842E-11     0.000000E+00     0.000000E+00
           CY     0.000000E+00     0.000000E+00     5.762829E-13     0.000000E+00     0.000000E+00
           CZ     6.671572E+03     7.156533E+03     7.156533E+03     0.000000E+00     0.000000E+00
           CMX    4.286052E+05     4.721812E+05     1.624215E+05     0.000000E+00     0.000000E+00
           CMY   -4.139441E+05    -4.793302E+05    -4.793302E+05     0.000000E+00     0.000000E+00
           CMZ    0.000000E+00     0.000000E+00     2.071765E-09     0.000000E+00     0.000000E+00

 A E R O D Y N A M I C   M O N I T O R   P O I N T   I N T E G R A T E D   L O A D S
                         CONFIGURATION = AEROSG2D     XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                           MACH = 5.000000E-01                Q = 2.571800E+00

        CONTROLLER STATE:
        CANARD   =   1.4529E-02        ANGLEA   =   3.7463E-02        URDD3    =   3.8616E+02

        MONITOR POINT NAME = AEROSG2D          COMPONENT =                   CLASS = COEFFICIENT
        LABEL = Full Vehicle Integrated Loads
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CX     0.000000E+00     0.000000E+00
           CY     0.000000E+00     0.000000E+00
           CZ     6.671572E+03     7.156533E+03
           CMX    4.286052E+05     4.721812E+05
           CMY   -4.139441E+05    -4.793302E+05
           CMZ    0.000000E+00     0.000000E+00

        MONITOR POINT NAME = CANARD            COMPONENT = 20                CLASS = HINGE MOMENT
        LABEL = CANARD   - Control Surface Hinge Moment
        CID =        1          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CMY    7.187500E+03     7.190499E+03

 A E R O S T A T I C   D A T A   R E C O V E R Y   O U T P U T   T A B L E S
                         CONFIGURATION = AEROSG2D     XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                           MACH = 5.000000E-01                Q = 2.571800E+00
                         CHORD = 9.5000E+01           SPAN = 3.1920E+02            AREA = 1.9829E+04

                                        TRANSFORMATION FROM REFERENCE TO WIND AXES:
                                ANGLE OF ATTACK   =  3.746328E-02 RADIANS (     2.146488 DEGREES)
                                ANGLE OF SIDESLIP =  0.000000E+00 RADIANS (     0.000000 DEGREES)

                                      { X }          [  0.999298  0.000000  0.037455 ]  { X }
                                      { Y }          [  0.000000  1.000000  0.000000 ]  { Y }
                                      { Z }WIND =    [ -0.037455  0.000000  0.999298 ]  { Z }REF

    STRUCTURAL  MONITOR POINT TOTAL VEHICLE COEFFICIENTS:
          AXIS         RIGID AIR  +  RESTRAINED INCR.  -  INERTIAL  +   RIGID-APPLIED + RESTRAINED INCR.  =  BALANCE
          ----         ---------     ----------------     --------      -------------   ----------------     -------
    BODY  CX          0.000000E+00     0.000000E+00    -2.503798E-16     0.000000E+00     0.000000E+00     2.503798E-16
    WIND  CD          4.899981E-03     3.561827E-04     5.256164E-03     0.000000E+00     0.000000E+00    -3.340281E-10

    BODY  CY          0.000000E+00     0.000000E+00     1.130050E-17     0.000000E+00     0.000000E+00    -1.130050E-17
    WIND  CY-WIND     0.000000E+00     0.000000E+00     1.130050E-17     0.000000E+00     0.000000E+00    -1.130050E-17

    BODY  CZ          1.308248E-01     9.509739E-03     1.403346E-01     0.000000E+00     0.000000E+00    -8.918239E-09
    WIND  CL          1.307330E-01     9.503066E-03     1.402361E-01     0.000000E+00     0.000000E+00    -8.911982E-09

    BODY  CMX         2.633034E-02     2.676987E-03     9.977977E-03     0.000000E+00     0.000000E+00     1.902935E-02
    WIND  CM-ROLL     2.631187E-02     2.675109E-03     9.970976E-03     0.000000E+00     0.000000E+00     1.901600E-02

    BODY  CMY        -8.544371E-02    -1.349657E-02    -9.894029E-02     0.000000E+00     0.000000E+00     1.061115E-08
    WIND  CM-PITCH   -8.544371E-02    -1.349657E-02    -9.894029E-02     0.000000E+00     0.000000E+00     1.061115E-08

    BODY  CMZ         0.000000E+00     0.000000E+00     1.272740E-16     0.000000E+00     0.000000E+00    -1.272740E-16
    WIND  CM-YAW     -9.861902E-04    -1.002653E-04    -3.737203E-04     0.000000E+00     0.000000E+00    -7.127352E-04

    AERODYNAMIC MONITOR POINT TOTAL VEHICLE COEFFICIENTS:
          AXIS         RIGID AIR  +  RESTRAINED INCR.  -  INERTIAL  +   RIGID-APPLIED + RESTRAINED INCR.  =  BALANCE
          ----         ---------     ----------------     --------      -------------   ----------------     -------
    BODY  CX          0.000000E+00     0.000000E+00           N/A              N/A              N/A        0.000000E+00
    WIND  CD          4.899981E-03     3.561827E-04           N/A              N/A              N/A        5.256163E-03

    BODY  CY          0.000000E+00     0.000000E+00           N/A              N/A              N/A        0.000000E+00
    WIND  CY-WIND     0.000000E+00     0.000000E+00           N/A              N/A              N/A        0.000000E+00

    BODY  CZ          1.308248E-01     9.509739E-03           N/A              N/A              N/A        1.403346E-01
    WIND  CL          1.307330E-01     9.503066E-03           N/A              N/A              N/A        1.402361E-01

    BODY  CMX         2.633034E-02     2.676987E-03           N/A              N/A              N/A        2.900733E-02
    WIND  CM-ROLL     2.631187E-02     2.675109E-03           N/A              N/A              N/A        2.898698E-02

    BODY  CMY        -8.544371E-02    -1.349657E-02           N/A              N/A              N/A       -9.894028E-02
    WIND  CM-PITCH   -8.544371E-02    -1.349657E-02           N/A              N/A              N/A       -9.894028E-02

    BODY  CMZ         0.000000E+00     0.000000E+00           N/A              N/A              N/A        0.000000E+00
    WIND  CM-YAW     -9.861902E-04    -1.002653E-04           N/A              N/A              N/A       -1.086455E-03
1606
721
948
3882
3882
  948
 1606
 721
7157
7157
  MONITOR POINT NAME = CAN_LIFT          COMPONENT = CAN_LIFT          CLASS = GENERAL
        LABEL = CAN_LIFT
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CZ     1.601506E+03     1.606107E+03
           CMX    9.470631E+04     9.498113E+04
           CMY    5.006467E+04     5.021215E+04

        MONITOR POINT NAME = WING_LIF          COMPONENT = WING_LIF          CLASS = GENERAL
        LABEL = WING_LIFT
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CZ     3.462840E+03     3.881783E+03
           CMX    3.107315E+05     3.531114E+05
           CMY   -4.292768E+05    -4.886566E+05

        MONITOR POINT NAME = WING_FUS          COMPONENT = WING_FUS          CLASS = GENERAL
        LABEL = WING_FUSE
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CZ     8.910090E+02     9.479647E+02
           CMX    1.336315E+04     1.422588E+04
           CMY   -6.600257E+04    -7.231875E+04

flap
A
B
C
D
E
 $ Monitor Points:
MONPNT1 FLAP_LD flap_region_total
        35      FLAP_LD 102     0.      0.      0.
$
$ AECOMP:
AELIST  25      115001  115002  115003  115006  115005  115004  115007
        115008  115009  116003  116002  116001  116004  116005  116006
        116009  116008  117001
AECOMP  FLAP_LD AELIST  25

 MONITOR POINT NAME = FLAP_LD           COMPONENT = FLAP_LD           CLASS = GENERAL
        LABEL = flap_region_total
        CID =        102        X =  0.00000E+00          Y =  0.00000E+00          Z =
          AXIS      RIGID AIR       ELASTIC REST.
          ----    -------------    -------------
           CZ     7.780567E+01     8.695660E+01
           CMY   -6.299542E+02    -7.044872E+02
87 lbf
-704 lbf in
Coord 16
$
$ Monitor Points:
MONPNT1 cl_spar cl_spar_loads
        35      cl_spar 16      0.      0.      0.
$
$ AECOMP:
SET1    103     37      39      41      43      45      47      106
        108     110     112     114     186     188     190     192
        196     198     200     202     267     268     269     270
        271     272     330     331     332     333     334     409
        410     411     412     419     420     421     422     589
        590     591     592     593     604     605     606     607
        619     620     621     622     635     636     637     638
        639     640     747     748     755     757     850     851
        860     861     928     929     930     940
AECOMP  cl_spar SET1    103
$
Z
MY
   MONITOR POINT NAME = CL_SPAR           COMPONENT = CL_SPAR           CLASS = GENERAL
        LABEL = CL_SPAR_LOADS
        CID =        16         X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.      INERTIAL      RIGID APPLIED    REST. APPLIED
          ----    -------------    -------------    -------------    -------------    -------------
           CZ     1.862206E+02     2.380110E+02     9.070477E+01     0.000000E+00     0.000000E+00
           CMY    1.811955E+04     2.279054E+04     7.388569E+03     0.000000E+00     0.000000E+00
CZ
CMY
x
y
CZ
CMY
Rigid AerodynamicLoads
Elastic Increments
Rigid AerodynamicLoads
Elastic Increments
Rigid AerodynamicLoads
Elastic Increments
Elastic Increments
Rigid AerodynamicLoads
$ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
$ MSC.Nastran External Loads File created by MSC.FlightLoads
$ version 2001.0.2 on 18:46:38 at 17-Aug-01.
$ Extracted from MSC.Patran database:
$ C:	ony_abbey	raining_material\FLDS	rainer_ac\ja_flutt_pk.db
$ MSC.Patran 2001 r2
$ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
CEND
SUBCASE 1
SUBTITLE=A1:Static Subcase
   LOAD = 1
BEGIN BULK
$   ( Aeroelastic Forces, Nodal Rigid Component )
FORCE   2       510     0       1.      0.+0    0.+0    6.710197
FORCE   2       531     0       1.      0.+0    0.+0    4.787435
FORCE   2       546     0       1.      0.+0    0.+0    12.40505
FORCE   2       561     0       1.      0.+0    0.+0    9.190941
...
$   ( Aeroelastic Restrained Forces, Nodal Elastic Component )
FORCE   3       510     0       1.      0.+0    0.+0    .7241759
FORCE   3       531     0       1.      0.+0    0.+0    .3625956
FORCE   3       546     0       1.      0.+0    0.+0    1.388873
FORCE   3       561     0       1.      0.+0    0.+0    .8576363
..
$   ( Aeroelastic Restrained Forces, Nodal Inertial Component )
FORCE   4       1       0       1.      4.0520-90.+0    425.0656
FORCE   4       2       0       1.      0.+0    0.+0    211.9077
FORCE   4       3       0       1.      -9.53-110.+0    300.0463
FORCE   4       4       0       1.      -2.38-110.+0    75.01158
..
LOAD    1       1.      1.      2       1.      3       -1.     4
ENDDATA
$ Aero DB FMS Statements
ASSIGN MASTER='wing_use_tail.master.1'
ASSIGN ADB='wing_fuse_tail.adb.1'
INIT ADB
ASSIGN AEDB='wing_fuse_tail.aedb.1'
INIT AEDB
$ Static AeroElastic Analysis
SOL 144
TITLE = MSC.Nastran Aeroelastic job created on 06-Jun-01 at 17:36:02
ECHO = NONE
AECONFIG = ts1
SUBCASE 1
$ Subcase name : level1
   SUBTITLE=Default
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 1
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL
...

$ Aero DB FMS Statements
ASSIGN ADB_1='wing_fuse_tail.master.1'
DBLOCATE LOGICAL=ADB_1 WHERE(DBSET='ADB' or DBSET='AEDB') $
$ Static AeroElastic Analysis
SOL 144
CEND
TITLE = MSC.Nastran Aeroelastic job created on 06-Jun-01 at 17:36:02
ECHO = NONE
AECONFIG = ts1
SUBCASE 1
$ Subcase name : level2_pullup
   SUBTITLE=Default
   SPC = 2
   DISPLACEMENT(SORT1,REAL)=ALL
   SPCFORCES(SORT1,REAL)=ALL
   STRESS(SORT1,REAL,VONMISES,BILIN)=ALL
TRIM = 1
AESYMXZ = Symmetric
AESYMXY = Asymmetric
SUPORT1 = 1
AEROF = ALL
APRES = ALL

...

Initial Trim Case
 12:01:19     0:14      269.0         0.0         7.8        0.0    AESTAT  91   (S)AESTATRSBEGN
 12:01:19     0:14      269.0         0.0         7.8        0.0    AESTATRS58      AELOOP  BEGN
 12:01:19     0:14      269.0         0.0         7.8        0.0    AESTATRS66      MAKETR  BEGN
 12:01:19     0:14      271.0         2.0         7.8        0.0    AESTATRS77      TRNSP   BEGN
 12:01:19     0:14      281.0        10.0         7.9        0.1    AESTATRS97      ADD     BEGN
 12:01:19     0:14      281.0         0.0         7.9        0.0    AESTATRS98      ADD     BEGN
 12:01:19     0:14      281.0         0.0         7.9        0.0    AESTATRS99      ADD     BEGN
..

 12:01:38     0:33      485.0         1.0        24.3        0.0    SEDRCVR 598     DBC     BEGN
 12:01:38     0:33      485.0         0.0        24.3        0.0    SEDRCVR 600     DBC     BEGN
 12:01:38     0:33      485.0         0.0        24.3        0.0    SEDRCVR 601     DBC     BEGN
 12:01:38     0:33      487.0         2.0        24.3        0.0    AESTAT  120  (S)PRTSUM  BEGN *
 12:01:38     0:33      487.0         0.0        24.3        0.0    PRTSUM  27      PROJVER BEGN
 12:01:38     0:33      487.0         0.0        24.3        0.0    PRTSUM  28      DBDICT  BEGN
 12:01:38     0:33      487.0         0.0        24.3        0.0    PRTSUM  29      PRTPARM BEGN
 12:01:38     0:33      487.0         0.0        24.3        0.0    AESTAT  121     EXIT    BEGN

Reusing the aedb for 2nd trim case:
 12:17:09     0:09      212.0         0.0         5.1        0.0    AESTAT  91   (S)AESTATRSBEGN
 12:17:09     0:09      212.0         0.0         5.1        0.0    AESTATRS58      AELOOP  BEGN
 12:17:09     0:09      212.0         0.0         5.1        0.0    AESTATRS66      MAKETR  BEGN
 12:17:09     0:09      213.0         1.0         5.1        0.0    AESTATRS317     MPYAD   BEGN *
 12:17:09     0:09      214.0         1.0         5.1        0.0    AESTATRS318     MPYAD   BEGN
 12:17:09     0:09      214.0         0.0         5.1        0.0    AESTATRS319     TRNSP   BEGN
 12:17:09     0:09      214.0         0.0         5.1        0.0    AESTATRS320     MATMOD  BEGN

...

 12:17:11     0:11      242.0         0.0         6.8        0.0    AESTAT  120  (S)PRTSUM  BEGN *
 12:17:11     0:11      242.0         0.0         6.8        0.0    PRTSUM  27      PROJVER BEGN
 12:17:11     0:11      242.0         0.0         6.8        0.0    PRTSUM  28      DBDICT  BEGN
 12:17:11     0:11      242.0         0.0         6.8        0.0    PRTSUM  29      PRTPARM BEGN
 12:17:11     0:11      242.0         0.0         6.8        0.0    AESTAT  121     EXIT    BEGN
6g
0.0
0.288 rad/s
free
free
1g
0.0
free
35 deg
free
1g
free
0.0
35 deg
free
6g
0.0
0.288 rad/s
-4.87
16.04 deg
1g
0.0
393 deg/s
35 deg
-8.24 deg
1g
280 deg/s2
0.0
35 deg
-1.63 deg
2
V
c
q

     BODY  CZ          1.227798E+00
   WIND  CL          1.180137E+00
Geometry Manipulation: Breaking Remaining Surfaces
Aerodynamic Mesh Divisions
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Curve  1
Surface  1
The single canard surface is now split into two
A query box asks if you wish to delete the original surface, yes in this case
Geometry Manipulation: Breaking Remaining Surfaces
Aerodynamic Mesh Divisions
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
The aero meshing strategy is shown here in terms of number of spanwise and chordwise aeor elements for each surface
Biasing could be used where steeper pressure gradients are anticipated
This will be used as an exercise for the student later
10 constant
3 constant
3 constant
5 constant
3 constant
3 constant
7 constant
This division ignored
3 constant
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
10 constant
3 constant
3 constant
5 constant
3 constant
3 constant
7 constant
This division ignored
3 constant
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability and Control Derivative Output
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
N O N - D I M E N S I O N A L   S T A B I L I T Y   A N D   C O N T R O L   D E R I V A T I V E
   C O E F F I C I E N T S

        CONFIGURATION = TS1          XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                          MACH = 5.0000E-01                    Q = 2.5718E+00
                         CHORD = 9.5000E+01           SPAN = 3.1920E+02            AREA = 1.9829E+04

Trim Cases
The .f06 file contains the stability and control derivative output for each trim condition.
The header summarises the trim condition:
Stability Derivatives
In our case we only have longitudinal stability derivatives.
The lift coefficient terms are:

The moment coefficient terms are:
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
N O N - D I M E N S I O N A L   S T A B I L I T Y   A N D   C O N T R O L   D E R I V A T I V E
   C O E F F I C I E N T S

        CONFIGURATION = TS1          XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                          MACH = 5.0000E-01                    Q = 2.5718E+00
                         CHORD = 9.5000E+01           SPAN = 3.1920E+02            AREA = 1.9829E+04

Trim Cases
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
N O N - D I M E N S I O N A L   S T A B I L I T Y   A N D   C O N T R O L   D E R I V A T I V E
   C O E F F I C I E N T S

        CONFIGURATION = TS1          XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                          MACH = 5.0000E-01                    Q = 2.5718E+00
                         CHORD = 9.5000E+01           SPAN = 3.1920E+02            AREA = 1.9829E+04

Trim Cases
Discussion of Lift Coefficient Derivatives
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability Derivatives in .f06
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
Trim Cases
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
 CONTROLLER STATE: INTERCEPT ONLY, ALL CONTROLLERS ARE ZERO

    TRIM VARIABLE   COEFFICIENT              RIGID                         ELASTIC                          INERTIAL
                                   UNSPLINED        SPLINED       RESTRAINED      UNRESTRAINED     RESTRAINED      UNRESTRAINED

    REF. COEFF.      CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.061313E-19    2.253668E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ        -2.192298E-14   -2.192298E-14    -2.352667E-14   -2.399215E-14    -1.279110E-17   -2.399215E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        2.565092E-14    2.565092E-14     2.801416E-14    2.837849E-14     3.980359E-17    2.836162E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    CANARD           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.858715E-19    1.349451E-02
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         2.358309E-01    2.358309E-01     2.103891E-01    1.993592E-01    -3.859970E-18    1.993592E-01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        4.983479E-01    4.983479E-01     5.322815E-01    5.458433E-01     1.216183E-17    5.448329E-01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    ANGLEA           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.195443E-20   -5.296896E-03
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         3.400623E+00    3.400623E+00     3.665259E+00    3.713126E+00    -1.157451E-18    3.713126E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -2.474000E+00   -2.474000E+00    -2.859308E+00   -2.887297E+00     3.962711E-18   -2.886900E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    SIDES            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
.....
z
C
0
Trim Cases
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope
 CONTROLLER STATE: INTERCEPT ONLY, ALL CONTROLLERS ARE ZERO

    TRIM VARIABLE   COEFFICIENT              RIGID                         ELASTIC                          INERTIAL
                                   UNSPLINED        SPLINED       RESTRAINED      UNRESTRAINED     RESTRAINED      UNRESTRAINED

    REF. COEFF.      CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.061313E-19    2.253668E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ        -2.192298E-14   -2.192298E-14    -2.352667E-14   -2.399215E-14    -1.279110E-17   -2.399215E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        2.565092E-14    2.565092E-14     2.801416E-14    2.837849E-14     3.980359E-17    2.836162E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    CANARD           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.858715E-19    1.349451E-02
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         2.358309E-01    2.358309E-01     2.103891E-01    1.993592E-01    -3.859970E-18    1.993592E-01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        4.983479E-01    4.983479E-01     5.322815E-01    5.458433E-01     1.216183E-17    5.448329E-01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    ANGLEA           CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     6.195443E-20   -5.296896E-03
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         3.400623E+00    3.400623E+00     3.665259E+00    3.713126E+00    -1.157451E-18    3.713126E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -2.474000E+00   -2.474000E+00    -2.859308E+00   -2.887297E+00     3.962711E-18   -2.886900E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    SIDES            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
.....
z
C
0

    ROLL             CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    PITCH            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.239254E-19   -1.409231E-01
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.121193E+01    1.121193E+01     1.205719E+01    1.231879E+01    -2.514021E-18    1.231879E+01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.439519E+01   -1.439519E+01    -1.564026E+01   -1.585319E+01     8.066646E-18   -1.584263E+01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    YAW              CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD1            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -4.625457E-19   -1.282328E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.119897E-14    1.119897E-14     1.202170E-14    1.227077E-14     9.899729E-18    1.227077E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.376156E-14   -1.376156E-14    -1.497476E-14   -1.517384E-14    -3.047236E-17   -1.516424E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD2            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD3            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -1.067984E-18   -1.301176E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.187761E-14    1.187761E-14    -8.996639E-08    1.300619E-14     3.634104E-04    1.300619E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.430087E-14   -1.430087E-14     1.153184E-06   -1.578820E-14    -2.562158E-04   -1.577846E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
 x accn term n/a
 y accn term n/a
Trim Cases
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope

    ROLL             CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    PITCH            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.239254E-19   -1.409231E-01
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.121193E+01    1.121193E+01     1.205719E+01    1.231879E+01    -2.514021E-18    1.231879E+01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.439519E+01   -1.439519E+01    -1.564026E+01   -1.585319E+01     8.066646E-18   -1.584263E+01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    YAW              CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD1            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -4.625457E-19   -1.282328E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.119897E-14    1.119897E-14     1.202170E-14    1.227077E-14     9.899729E-18    1.227077E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.376156E-14   -1.376156E-14    -1.497476E-14   -1.517384E-14    -3.047236E-17   -1.516424E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD2            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD3            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -1.067984E-18   -1.301176E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.187761E-14    1.187761E-14    -8.996639E-08    1.300619E-14     3.634104E-04    1.300619E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.430087E-14   -1.430087E-14     1.153184E-06   -1.578820E-14    -2.562158E-04   -1.577846E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
Trim Cases
Stability Derivatives in .f06 (ctd.)
Stability Derivatives in .f06 (ctd.)
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope

    URDD4            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD5            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.116072E-03   -1.284997E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.155316E-14    1.155316E-14    -6.621490E-04    1.265632E-14    -2.434050E-02    1.265632E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.400548E-14   -1.400548E-14     8.048715E-04   -1.545924E-14     7.384621E-02   -1.544961E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD6            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
Trim Cases
Trim Variables in .f06
The aircraft is flying with a small positive incidence of 2.15 degrees and Canard positive incidence of 0.83 degrees
Check of Lift Curve Slope

    ROLL             CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    PITCH            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.239254E-19   -1.409231E-01
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.121193E+01    1.121193E+01     1.205719E+01    1.231879E+01    -2.514021E-18    1.231879E+01
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.439519E+01   -1.439519E+01    -1.564026E+01   -1.585319E+01     8.066646E-18   -1.584263E+01
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    YAW              CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD1            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -4.625457E-19   -1.282328E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.119897E-14    1.119897E-14     1.202170E-14    1.227077E-14     9.899729E-18    1.227077E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.376156E-14   -1.376156E-14    -1.497476E-14   -1.517384E-14    -3.047236E-17   -1.516424E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD2            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD3            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00    -1.067984E-18   -1.301176E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.187761E-14    1.187761E-14    -8.996639E-08    1.300619E-14     3.634104E-04    1.300619E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.430087E-14   -1.430087E-14     1.153184E-06   -1.578820E-14    -2.562158E-04   -1.577846E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD4            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD5            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     1.116072E-03   -1.284997E-16
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         1.155316E-14    1.155316E-14    -6.621490E-04    1.265632E-14    -2.434050E-02    1.265632E-14
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY       -1.400548E-14   -1.400548E-14     8.048715E-04   -1.545924E-14     7.384621E-02   -1.544961E-14
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00

    URDD6            CX         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CY         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CZ         0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMX        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMY        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
                     CMZ        0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00     0.000000E+00    0.000000E+00
Trim Cases
Check of Lift Curve Slope

     TRIM ALGORITHM USED: LINEAR TRIM SOLUTION WITHOUT REDUNDANT CONTROL SURFACES.

                                                      AEROELASTIC TRIM VARIABLES

                                  ID     LABEL                 TYPE        TRIM STATUS      VALUE OF UX

                                         INTERCEPT          RIGID BODY           FIXED      1.000000E+00
                                   1     CANARD        CONTROL SURFACE            FREE      1.452887E-02  RADIANS
                                   2     ANGLEA             RIGID BODY            FREE      3.746328E-02  RADIANS
                                   3     SIDES              RIGID BODY           FIXED      0.000000E+00  RADIANS
                                   4     ROLL               RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   5     PITCH              RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   6     YAW                RIGID BODY           FIXED      0.000000E+00  NONDIMEN. RATE
                                   7     URDD1              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                   8     URDD2              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                   9     URDD3              RIGID BODY           FIXED      3.861600E+02  LENGTH/S/S
                                  10     URDD4              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                  11     URDD5              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
                                  12     URDD6              RIGID BODY           FIXED      0.000000E+00  LENGTH/S/S
Trim Cases
Trim Cases
Trim Cases

                                           CONTROL SURFACE POSITION AND HINGE MOMENT RESULTS

                            ACTIVE LIMITS ARE FLAGGED WITH AN (A),  VIOLATED LIMITS ARE FLAGGED WITH A (V).

                                                POSITION                                         HINGE MOMENT
          CONTROL SURFACE      LOWER LIMIT       VALUE         UPPER LIMIT        LOWER LIMIT       VALUE         UPPER LIMIT
              CANARD         -9.000020E+01    1.452887E-02    9.000021E+01            N/A        9.530430E+03         N/A
Trim Cases

 S T R U C T U R A L   M O N I T O R   P O I N T   I N T E G R A T E D   L O A D S
                         CONFIGURATION = AEROSG2D     XY-SYMMETRY = ASYMMETRIC     XZ-SYMMETRY = SYMMETRIC
                                           MACH = 5.000000E-01                Q = 2.571800E+00

        CONTROLLER STATE:
        CANARD   =   1.4529E-02        ANGLEA   =   3.7463E-02        URDD3    =   3.8616E+02

         MONITOR POINT NAME = AEROSG2D          COMPONENT =                   CLASS = COEFFICIENT
        LABEL = Full Vehicle Integrated Loads
        CID =        0          X =  0.00000E+00          Y =  0.00000E+00          Z =  0.00000E+00

          AXIS      RIGID AIR       ELASTIC REST.      INERTIAL      RIGID APPLIED    REST. APPLIED
          ----    -------------    -------------    -------------    -------------    -------------
           CX     0.000000E+00     0.000000E+00    -1.276842E-11     0.000000E+00     0.000000E+00
           CY     0.000000E+00     0.000000E+00     5.762829E-13     0.000000E+00     0.000000E+00
           CZ     6.671572E+03     7.156533E+03     7.156533E+03     0.000000E+00     0.000000E+00
           CMX    4.286052E+05     4.721812E+05     1.624215E+05     0.000000E+00     0.000000E+00
           CMY   -4.139441E+05    -4.793302E+05    -4.793302E+05     0.000000E+00     0.000000E+00
           CMZ    0.000000E+00     0.000000E+00     2.071765E-09     0.000000E+00     0.000000E+00