| Real | alphaStall_deg (from CoefficientsAndDerivativesSimple) | | stall angle of attack |
| Real | CL0 (from CoefficientsAndDerivativesSimple) | | |
| Real | CLa (from CoefficientsAndDerivativesSimple) | | CL alpha slope |
| Real | CD0 (from CoefficientsAndDerivativesSimple) | | minimum drag |
| Real | CDCL (from CoefficientsAndDerivativesSimple) | | CL^2 term for drag polar |
| Real | CYb (from CoefficientsAndDerivativesSimple) | | side slipe effect on side force |
| Real | Clp (from CoefficientsAndDerivativesSimple) | | roll damping, <0 for stability |
| Real | Clda (from CoefficientsAndDerivativesSimple) | | aileron effect on roll |
| Real | Cmq (from CoefficientsAndDerivativesSimple) | | pitch damping, <0 for stability |
| Real | Cma (from CoefficientsAndDerivativesSimple) | | alpha effect on pitch, <0 for stability |
| Real | Cmde (from CoefficientsAndDerivativesSimple) | | elevator effect on pitch |
| Real | Cnb (from CoefficientsAndDerivativesSimple) | | weather cocking stability >0 for stability |
| Real | Cnr (from CoefficientsAndDerivativesSimple) | | yaw damping, <0 for stability |
| Real | Cndr (from CoefficientsAndDerivativesSimple) | | rudder effecto on yaw |
| SI.Force[3] | F_b (from ForceMoment) | | |
| SI.Torque[3] | M_b (from ForceMoment) | | |
| World.WorldBase | world (from ForceMoment) | | |
| SI.Velocity[3] | vR_b (from ForceMoment) | | relative air velocity resolved in body frame |
| SI.Acceleration[3] | aR_b (from ForceMoment) | | relative air acceleration resolved in body frame |
| SI.Velocity | vt (from ForceMoment) | | true air velocity |
| SI.Acceleration | vtDot (from ForceMoment) | | true air velocity derivative |
| SI.Pressure | qBar (from ForceMoment) | | dynamics pressure |
| SI.Angle | alpha (from ForceMoment) | | angle of attack |
| SI.AngularVelocity | alphaDot (from ForceMoment) | | derivative of angle of attack |
| SI.Angle | beta (from ForceMoment) | | side slip angle |
| SI.AngularVelocity | betaDot (from ForceMoment) | | derivative of side slip angle |
| SI.AngularVelocity | p (from ForceMoment) | | body roll rate |
| SI.AngularVelocity | q (from ForceMoment) | | body pitch rate |
| SI.AngularVelocity | r (from ForceMoment) | | body yaw rate |
| SI.Angle | alpha_deg (from ForceMoment) | | angle of attack, deg |
| SI.Angle | beta_deg (from ForceMoment) | | side slip, deg |
| Real[3,3] | C_bs (from ForceMoment) | | stability to body frame |
| Real[3,3] | C_bw (from ForceMoment) | | wind to body frame |
| Real[3] | wind (from ForceMoment) | | wind |
| Real | CL (from ForceMomentStabilityFrame) | | |
| Real | CD (from ForceMomentStabilityFrame) | | |
| Real | CY (from ForceMomentStabilityFrame) | | |
| Real | Cl (from ForceMomentStabilityFrame) | | |
| Real | Cm (from ForceMomentStabilityFrame) | | |
| Real | Cn (from ForceMomentStabilityFrame) | | |
| Real | CL_Basic (from CoefficientsAndDerivatives) | | basic lift coefficient |
| Real | dCL_Flap (from CoefficientsAndDerivatives) | | change in lift coefficient due to flaps |
| Real | dCL_Elevator (from CoefficientsAndDerivatives) | | change in lift coefficient due to elevator |
| Real | dCL_PitchRate (from CoefficientsAndDerivatives) | | change in lift coefficient due to pitch rate |
| Real | dCL_AlphaDot (from CoefficientsAndDerivatives) | | change in lift coefficient due to aoa rate |
| Real | CD_Basic (from CoefficientsAndDerivatives) | | basic drag coefficient |
| Real | dCD_Flap (from CoefficientsAndDerivatives) | | change in drag coefficient due to flaps |
| Real | dCD_Elevator (from CoefficientsAndDerivatives) | | change in drag coefficient due to elevator |
| Real | dCY_Beta (from CoefficientsAndDerivatives) | | change in side force coefficient due to side slip angle |
| Real | dCY_RollRate (from CoefficientsAndDerivatives) | | change in side force coefficient due to roll rate |
| Real | dCl_Aileron (from CoefficientsAndDerivatives) | | change in roll moment coefficient due to aileron |
| Real | dCl_Beta (from CoefficientsAndDerivatives) | | change in roll moment coefficient due to side slip angle |
| Real | dCl_RollRate (from CoefficientsAndDerivatives) | | change in roll moment coefficient due to roll rate |
| Real | dCl_YawRate (from CoefficientsAndDerivatives) | | change in roll moment coefficient due to yaw rate |
| Real | Cm_Basic (from CoefficientsAndDerivatives) | | basic pitch moment coefficient |
| Real | dCm_Flap (from CoefficientsAndDerivatives) | | change in pitch moment coefficient due to flaps |
| Real | dCm_Elevator (from CoefficientsAndDerivatives) | | change in pitch moment coefficient due to elevator |
| Real | dCm_PitchRate (from CoefficientsAndDerivatives) | | change in pitch moment coefficient due to pitch rate |
| Real | dCm_AlphaDot (from CoefficientsAndDerivatives) | | change in pitch moment coefficient due to aoa rate |
| Real | dCn_Aileron (from CoefficientsAndDerivatives) | | change in yaw moment coefficient due to aileron |
| Real | dCn_Rudder (from CoefficientsAndDerivatives) | | change in yaw moment coefficient due to rudder |
| Real | dCn_Beta (from CoefficientsAndDerivatives) | | change in yaw moment coefficient due to side slip angle |
| Real | dCn_RollRate (from CoefficientsAndDerivatives) | | change in yaw moment coefficient due to roll rate |
| Real | dCn_YawRate (from CoefficientsAndDerivatives) | | change in yaw moment coefficient due to yaw rate |
| Real | flap_deg (from Controls) | | flap |
| Real | aileron_deg (from Controls) | | aileron |
| Real | elevator_deg (from Controls) | | elevator |
| Real | rudder_deg (from Controls) | | rudder |
| Real | alpha_deg_effective | | |