Last updated June 2, 2000
The linear aerodynamics model uses stability derivatives to approximate actual aircraft behavior. The F-104 linear model is based on the following flight conditions (cruise):
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
| h | Altitude | altitude above sea level | ft | 55000 | Roskam pg 529 |   | Alpha | angle of attack | deg | 2 | Roskam pg 529 | 
| V   | V_true_kts | velocity (true air speed) | kts | 1031.4 | Roskam pg 529 | Mach 1.8 | 
| q | Dynamic_pressure | dynamic pressure | lb/ft2 | 434.5 | Roskam pg 529 | |
| C.G. | - | center of gravity location | %   | 7 | Roskam pg 529 | |
| CL | CL | lift coefficient | - | ? | not available | |
| CD | CD | drag coefficient | - | ? | not available | |
| Cm | Cm | pitching moment coefficient | - | ? | not available | |
The data input into the simulator is listed in the following tables:
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
| b | bw | wingspan | ft | 21.9 | Roskam pg 529 | |
|   | cbar | wing mean aerodynamic chord | ft | 9.6 | Roskam pg 529 | |
| S | Sw | wing surface area | ft2 | 196 | Roskam pg 529 | |
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
|  emax | demax | maximum elevator deflection | deg | +20 | - | guess | 
|  emin | demin | minimum elevator deflection | deg | -20 | - | guess | 
|  amax | damax | maximum aileron deflection | deg | +20 | - | guess | 
|  amin | damin | minimum aileron deflection | deg | -20 | - | guess | 
|  rmax | drmax | maximum rudder deflection | deg | +20 | - | guess | 
|  rmin | drmin | minimum rudder deflection | deg | -20 | - | guess | 
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
| W | Weight | weight at flight condition | lb | 16300 | Roskam pg 529 | converted to Mass [slug/ft3] in code | 
| Ixx | I_xx | roll inertia | slug ft2 | 3600 | Roskam pg 529 | |
| Iyy | I_yy | pitch inertia | slug ft2 | 59000 | Roskam pg 529 | |
| Izz | I_zz | yaw inertia | slug ft2 | 60000 | Roskam pg 529 | |
| Ixz | I_xz | lateral cross inertia | slug ft2 | 0 | Roskam pg 529 | |
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
| Tmax | simpleSingleMaxThrust | maximum thrust | lb | 5050 | Roskam pg 530 | estimated from CTx at sea level | 
| Tmax | simpleSingleMaxThrust | maximum thrust | lb | 7800 | MAM site | engine rating (F-104A) | 
| Tmax | simpleSingleMaxThrust | maximum thrust | lb | 15800 | MAM site | engine rating (F-104G) | 
| Tmax | simpleSingleMaxThrust | maximum thrust | lb | 18800 | MAM site | engine rating (F-104S) | 
|  | ||||||
| Variable | Variable in Code | Description | Units | Value(s) | Source | Notes | 
|---|---|---|---|---|---|---|
| CD0 | CDo | drag coefficient at  =0 | - | 0.048 | Roskam pg 530 | |
| CD   | CD_a | drag curve slope | 1/rad | 0.384 | Roskam pg 530 | |
| CD  e | CD_de | drag due to elevator | 1/rad | 0 | Roskam pg 530 |  e positive down | 
| CL0 | CLo | lift coefficient at  =0 | - | 0.122 | Roskam pg 530 | |
| CL   | CL_a | lift curve slope | 1/rad | 2.005 | Roskam pg 530 | |
| CL   | CL_adot | lift due to angle of attack rate | 1/rad | 0.82 | Roskam pg 530 | |
| CLq | CL_q | lift due to pitch rate | 1/rad | 1.9 | Roskam pg 530 | |
| CL  e | CL_de | lift due to elevator | 1/rad | 0.523 | Roskam pg 530 |  e positive down | 
| Cm0 | Cmo | pitch moment coefficient at  =0 | - | -0.028 | Roskam pg 530 | |
| Cm   | Cm_a | pitch moment due to angle of attack | 1/rad | -1.308 | Roskam pg 530 | |
| Cm   | Cm_adot | pitch moment due to angle of attack rate | 1/rad | -2.05 | Roskam pg 530 | |
| Cmq | Cm_q | pitch moment due to pitch rate | 1/rad | -4.83 | Roskam pg 530 | |
| Cm  e | Cm_de | pitching moment due to elevator | 1/rad | -1.31 | Roskam pg 530 |  e positive down | 
| CY   | CY_beta | side force fue to sideslip angle | 1/rad | -1.045 | Roskam pg 531 | |
| CYp | CY_p | side force due to roll rate | 1/rad | 0 | Roskam pg 531 | |
| CYr | CY_r | side force due to yaw rate | 1/rad | 0 | Roskam pg 531 | |
| CY  a | CY_da | side force due to aileron | 1/rad | 0 | Roskam pg 531 |  a positive right aileron up | 
| CY  r | CY_dr | side force due to rudder | 1/rad | 0.87 | Roskam pg 531 |  r positive left | 
| Cl   | Cl_beta | dihedral effect | 1/rad | -0.093 | Roskam pg 531 | |
| Clp | Cl_p | roll damping | 1/rad | -0.272 | Roskam pg 531 | |
| Clr | Cl_r | roll moment due to yaw rate | 1/rad | 0.154 | Roskam pg 531 | |
| Cl  a | Cl_da | roll moment due to aileron | 1/rad | -0.0173 | Roskam pg 531 |  a positive right aileron up | 
| Cl  r | Cl_dr | roll moment due to rudder | 1/rad | 0.0079 | Roskam pg 531 |  r positive left | 
| Cn   | Cn_beta | weathercock stability | 1/rad | 0.242 | Roskam pg 531 | |
| Cnp | Cn_p | adverse yaw | 1/rad | -0.093 | Roskam pg 531 | |
| Cnr | Cn_r | yaw damping | 1/rad | -0.649 | Roskam pg 531 | |
| Cn  a | Cn_da | yaw moment due to aileron | 1/rad | -0.0025 | Roskam pg 531 |  a positive right aileron up | 
| Cn  r | Cn_dr | yaw moment due to rudder | 1/rad | -0.0435 | Roskam pg 531 |  r positive left |