Author: Bruce Jackson
Created: 28-MAR-2002
Reference 1. Stevens, Brian L. and Lewis, Frank L.: Aircraft Control and Simulation. ISBN O-471-61397-5, 1992.
Reference 2. Garza, Fredrico R.; and Morelli, Eugene A.: A Collection of Nonlinear Aircraft Simulations in MATLAB. NASA TM-2003-212145, JAN-2003.
Reference 3. Morelli, Eugene A.: f16_aero.m. 17-JUN-1995.
Reference 4. Morelli, Eugene A.: f16_aero_setup.m. 17-JUN-1995.
Symbol | Name | Units | Sign | Initial value | Depends on |
---|---|---|---|---|---|
absbeta | deg |
| beta |
||
Absolute value of angle-of-sideslip, deg. | |||||
absCl0 |
| ||||
Absolute value of rolling moment coefficient | |||||
absCn0 |
| ||||
Absolute value of yawing moment coefficient | |||||
Angle_of_Attack_deg | α | deg |
| ||
Instantaneous true angle-of-attack, in degrees | |||||
Angle_of_Sideslip_deg | β | deg | +wind in right ear |
| |
Instantaneous true angle-of-sideslip, in degrees | |||||
b2v |
| bspan tvt |
|||
Wing span over 2 times velocity. Used for coefficient normalization. | |||||
bspan | ft | 30. | |||
Length of aerodynamic span, ft | |||||
cbar | ft | 11.32 | |||
Length of aerodynamic chord, ft | |||||
Cl0 | +right wing down |
| absCl0 absCl0 beta |
||
Basic coefficient of moment around the X-body direction (roll) (+RWD) | |||||
Cl1 |
| clt dail dclda dcldr drdr |
|||
Initial value of rolling moment, less damping terms | |||||
ClDA | per deg | +right/+left |
| ||
Control power derivative: rolling moment per deg of aileron deflection | |||||
ClDR | per deg | +right/+left |
| ||
Control power derivative: rolling moment per deg of rudder deflection | |||||
CLL | +RWD |
| b2v cl1 clp clr p r |
||
Total coefficient of moment around the body X-axis (rolling moment) | |||||
CLM | +ANU |
| cmq cmt cq2v cz xcg xcgr |
||
Total coefficient of moment around the body Y-axis (pitching moment) | |||||
CLN | +ANR |
| b2v bspan cbar cn1 cnp cnr cy p r xcg xcgr |
||
Total coefficient of moment around the body Z-axis (yawing moment) | |||||
Clp | per rad | +right/+right |
| ||
Damping derivative: rolling moment increment per radian/sec of roll rate | |||||
Clr | per rad | +right/+right |
| ||
Damping derivative: rolling moment increment per radian/sec of yaw rate | |||||
Cm0 | +nose up |
| |||
Basic coefficient of moment around the Y-body direction (pitch) (+ANU) | |||||
Cmq | per rad | +up/+up |
| ||
Damping derivative: pitching moment increment per radian/sec of pitch rate | |||||
Cn |
| cnt dail dcnda dcndr drdr |
|||
Initial value of rolling moment coefficient without damping terms | |||||
Cn0 | +nose right |
| absCn0 absCn0 beta |
||
Basic coefficient of moment around the Z-body direction (yaw) (+RWD) | |||||
CnDA | per deg | +right/+left |
| ||
Control power derivative: yawing moment per deg of aileron deflection | |||||
CnDR | per deg | +right/+left |
| ||
Control power derivative: yawing moment per deg of rudder deflection | |||||
Cnp | per rad | +right/+right |
| ||
Damping derivative: yawing moment increment per radian/sec of roll rate | |||||
Cnr | per rad | +right/+right |
| ||
Damping derivative: yawing moment increment per radian/sec of yaw rate | |||||
cq2v |
| cbar q tvt |
|||
Chord times pitch rate over 2 times velocity. Used to normalize aero coefficients. | |||||
CX | +FWD |
| cq2v cxq cxt |
||
Total coefficient of force along the body X-axis. | |||||
CX0 | +forward |
| |||
Basic coefficient of force in the X-body direction (+FWD). Function table based on angle of attack and elevator deflection. | |||||
CXq | per rad | +fwd/+up |
| ||
Damping derivative: axial force increment per radian/sec of pitch rate | |||||
CY | +RIGHT |
| b2v cy0 cyp cyr p r |
||
Total coefficient of force along the body Y-axis | |||||
CY0 | +right |
| beta dail drdr |
||
Basic coefficient of force in the Y-body direction (+right). Function of sideslip angle, aileron and rudder deflection. | |||||
CYp | per rad | +right/+right |
| ||
Damping derivative: lateral force increment per radian/sec of roll rate | |||||
CYr | per rad | +right/+right |
| ||
Damping derivative: lateral force increment per radian/sec of yaw rate | |||||
CZ | +DOWN |
| cq2v cz1 czq |
||
Total coefficient of force along the body Z-axis. | |||||
CZ0 | +down |
| |||
Basic coefficient of force in the Z-body direction (+DWN). Function table based on angle of attack and elevator deflection. | |||||
CZ1 | +down |
| beta czt del rtd |
||
Coefficient of force in the Z-body direction, modified from basic CZ0 to include effects of sideslip and elevator deflection. | |||||
CZq | per rad | +down/+up |
| ||
Damping derivative: vertical force increment per radian/sec of pitch rate | |||||
dail |
| ail |
|||
Normalized aileron deflection. | |||||
del |
| el |
|||
Normalized elevator deflection (note range is beyond breakpoint range) | |||||
delta aileron | δa | deg | +left roll |
| |
Aileron deflection angle, in degrees (+LWD) | |||||
delta elevator | δe | deg | +trailing edge down |
| |
Elevator deflection angle, in degrees (+ED) | |||||
delta rudder | δr | deg | +TEL |
| |
Rudder deflection angle, in degrees (+TEL) | |||||
drdr |
| rdr |
|||
Normalized rudder deflection. | |||||
rtd | deg/rad |
| |||
Conversion constant from radians to degrees | |||||
s_Body_Pitch_Rate_rad_p_s | q | rad/sec | +aircraft nose up |
| |
Body pitch rate, rad/sec | |||||
s_Body_Roll_Rate_rad_p_s | p | rad/sec | +right wing down |
| |
Body roll rate, rad/sec | |||||
s_Body_Yaw_Rate_rad_p_s | r | rad/sec | +aircraft nose right |
| |
Body yaw rate, rad/sec | |||||
True_Airspeed_f_p_s | ft/sec |
| |||
True airspeed, ft/sec | |||||
tvt | ft/sec |
| vt |
||
Twice velocity. | |||||
Xcg | fract | +aft |
| ||
CG location relative to wing leading edge, expressed as a fraction of aerodynamic chord length | |||||
xcgr | fract | 0.35 | |||
Default location of center of gravity relative to wing leading edge, expressed as a fraction of aerodynamic chord length. |
Basic Cl | absCl0 = f(absbeta, α) | |
where: | 0.0 <= absbeta <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Basic coefficient of rolling moment as a function of angle of attack and sideslip angle |
Basic Cm | Cm0 = f(δe, α) | |
where: | -24.0 <= δe <= 24.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Basic coefficient of pitching-moment as a function of angle of attack and elevator |
Basic Cn | absCn0 = f(absbeta, α) | |
where: | 0.0 <= absbeta <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Basic coefficient of yawing moment as a function of angle of attack and sideslip angle |
Basic CX | CX0 = f(δe, α) | |
where: | -24.0 <= δe <= 24.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Basic coefficient of X-force table as a function of angle of attack and elevator |
Basic CZ | CZ0 = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Basic coefficient of Z-force table as a function of angle of attack |
Clp | Clp = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: rolling moment due to roll rate as a function of angle-of-attack |
Clr | Clr = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: rolling moment due to yaw rate as a function of angle-of-attack |
Cmq | Cmq = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: pitching moment due to pitch rate as a function of angle-of-attack |
Cnp | Cnp = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: yawing moment due to roll rate as a function of angle-of-attack |
Cnr | Cnr = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: yawing moment due to yaw rate as a function of angle-of-attack |
CXq | CXq = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: axial force due to pitch rate as a function of angle-of-attack |
CYp | CYp = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: lateral force due to roll rate as a function of angle-of-attack |
CYr | CYr = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: lateral force due to yaw rate as a function of angle-of-attack |
CZq | CZq = f(α) | |
where: | -10.0 <= α <= 45.0; extrapolate neither | |
Damping derivative: normal force due to pitch rate as a function of angle-of-attack |
dlda | ClDA = f(β, α) | |
where: | -30.0 <= β <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Rolling moment increment due to aileron deflection as a function of angles of attack and sideslip |
dldr | ClDR = f(β, α) | |
where: | -30.0 <= β <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Rolling moment increment due to rudder deflection as a function of angles of attack and sideslip |
dnda | CnDA = f(β, α) | |
where: | -30.0 <= β <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Yawing moment increment due to aileron deflection as a function of angles of attack and sideslip |
dndr | CnDR = f(β, α) | |
where: | -30.0 <= β <= 30.0; extrapolate neither | |
-10.0 <= α <= 45.0; extrapolate neither | ||
Yawing moment increment due to rudder deflection as a function of angles of attack and sideslip |