Last updated April 10, 2000
The linear aerodynamics model uses stability derivatives to approximate actual aircraft behavior. The Pioneer linear model is based on the following flight conditions:
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
| h | Altitude | altitude above sea level | ft | 0 | - | assuming sea level |
|
Alpha | angle of attack | deg | 6 | Bray pg 33 |
V
|
V_true_kts | velocity (true air speed) | kts | 66 | Bray pg 33 | |
| q | Dynamic_pressure | dynamic pressure | lb/ft2 | 14.7 | - | assuming sea level |
| C.G. | - | center of gravity location |
%
|
33 | Bray pg 33 | |
| CL | CL | lift coefficient | - | 0.945 | Bray pg 33 | |
| CD | CD | drag coefficient | - | 0.090 | Bray pg 33 | |
| Cm | Cm | pitching moment coefficient | - | 0.012 | Bray pg 33 | |
The data input into the simulator is listed in the following tables:
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
| b | bw | wingspan | ft | 16.9 | Bray pg 33 | |
|
cbar | wing mean aerodynamic chord | ft | 1.80 | Bray pg 33 | |
| S | Sw | wing surface area | ft2 | 30.42 | Bray pg 33 | |
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
emax
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demax | maximum elevator deflection | deg | +20 | Bray pg 31 | |
emin
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demin | minimum elevator deflection | deg | -20 | Bray pg 31 | |
amax
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damax | maximum aileron deflection | deg | +20 | Bray pg 31 | |
amin
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damin | minimum aileron deflection | deg | -20 | Bray pg 31 | |
rmax
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drmax | maximum rudder deflection | deg | +20 | Bray pg 31 | |
rmin
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drmin | minimum rudder deflection | deg | -20 | Bray pg 31 | |
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
| GTOW | Weight | gross takeoff weight | lb | 420 | Bray pg 33 |
converted to Mass [slug/ft3] in code |
| Ixx | I_xx | roll inertia | slug ft2 | 34.832 |
IAI (manufacturer) MSS notes |
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| Iyy | I_yy | pitch inertia | slug ft2 | 67.08 |
IAI (manufacturer) MSS notes |
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| Izz | I_zz | yaw inertia | slug ft2 | 82.22 |
IAI (manufacturer) MSS notes |
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| Ixz | I_xz | lateral cross inertia | slug ft2 | -4.902 |
IAI (manufacturer) MSS notes |
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
| Tmax | simpleSingleMaxThrust | maximum thrust | lb | 150 | - |
approximated from max power of 27 hp |
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| Variable |
Variable in Code |
Description | Units | Value(s) | Source | Notes |
|---|---|---|---|---|---|---|
| CD0 | CDo |
drag coefficient at =0
|
- | 0.060 | Bray pg 33 | |
CD
|
CD_a | drag curve slope | 1/rad | 0.430 | Bray pg 33 | |
CD e
|
CD_de | drag due to elevator | 1/rad | 0.018 | Bray pg 33 |
e positive down
|
| CL0 | CLo |
lift coefficient at =0
|
- | 0.385 | Bray pg 33 | |
CL
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CL_a | lift curve slope | 1/rad | 4.78 | Bray pg 33 | |
CL
|
CL_adot | lift due to angle of attack rate | 1/rad | 2.42 | Bray pg 33 | |
| CLq | CL_q | lift due to pitch rate | 1/rad | 8.05 | Bray pg 33 | |
CL e
|
CL_de | lift due to elevator | 1/rad | 0.401 | Bray pg 33 |
e positive down
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| Cm0 | Cmo |
pitch moment coefficient at =0
|
- | 0.194 | Bray pg 33 | |
Cm
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Cm_a | pitch moment due to angle of attack | 1/rad | -2.12 | Bray pg 33 | |
Cm
|
Cm_adot | pitch moment due to angle of attack rate | 1/rad | -11.0 | Bray pg 33 | |
| Cmq | Cm_q | pitch moment due to pitch rate | 1/rad | -36.6 | Bray pg 33 | |
Cm e
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Cm_de | pitching moment due to elevator | 1/rad | -1.76 | Bray pg 33 |
e positive down
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CY
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CY_beta | side force fue to sideslip angle | 1/rad | -0.819 | Bray pg 33 | |
| CYp | CY_p | side force due to roll rate | 1/rad | none | not available | |
| CYr | CY_r | side force due to yaw rate | 1/rad | none | not available | |
CY a
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CY_da | side force due to aileron | 1/rad | none | not available | |
CY r
|
CY_dr | side force due to rudder | 1/rad | 0.191 | Bray pg 33 |
r positive left
|
Cl
|
Cl_beta | dihedral effect | 1/rad | -0.023 | Bray pg 33 | |
| Clp | Cl_p | roll damping | 1/rad | -0.450 | Bray pg 33 | |
| Clr | Cl_r | roll moment due to yaw rate | 1/rad | 0.265 | Bray pg 33 | |
Cl a
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Cl_da | roll moment due to aileron | 1/rad | -0.161 | Bray pg 33 |
a positiveright aileron up |
Cl r
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Cl_dr | roll moment due to rudder | 1/rad | -0.00229 | Bray pg 33 |
r positive left
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Cn
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Cn_beta | weathercock stability | 1/rad | 0.109 | Bray pg 33 | |
| Cnp | Cn_p | adverse yaw | 1/rad | -0.110 | Bray pg 33 | |
| Cnr | Cn_r | yaw damping | 1/rad | -0.200 | Bray pg 33 | |
Cn a
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Cn_da | yaw moment due to aileron | 1/rad | 0.020 | Bray pg 33 |
a positiveright aileron up |
Cn r
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Cn_dr | yaw moment due to rudder | 1/rad | -0.0917 | Bray pg 33 |
r positive left
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