derivative SSPNE semispan exposed panel Cnr Cy from Yaw Rate length derivative SSPN theoretical semispan Cm_Total Pitching Moment • Total exposed panel length Coefficient due to: SAVSI inboard sweep angle Cm from Basic geometry Cmα CHSTAT reference chord station Cm from Flap deflection Cmδf (0.25) TWISTA twist angle Cm from Elevator Cmδe deflection DHDADI dihedral angle Cmq Cm from Pitch Rate derivative TYPE wing shape (1=straight Cm from Angle of Attack Cmαdot tapered, Rate derivative 2=delta,3=cranked) Cl_Total Rolling Moment • Total Coefficient due to: [Aileron, Wing Cl from Aileron Deflection Clδa Flaps, and Elevators] NDELTA # of deflectionangles to Cl from Sideslip Clβ test DELTA specific deflection Clp Cl from Roll Rate angles derivative SPANFI dimension of flap Clr Cl from Yaw Rate derivative SPANFO Cn_Total Yawing Moment • Total Coefficient CHRDFI Cn from Aileron deflection (Cyδa) CHRDFO Cn from Sideslip (Cyβ) NTYPE nose type (1=round, v(Cyp) Cn from Roll Rate 2=elliptical, 3=sharp) derivative CB average balance chord (Cyr) Cn from Yaw Rate derivative TC average thickness Misc • PHETE tangent of arifoil Horizontal Tail Downwash ε trailing edge angle Angle PHETEP tangent of arifoil Derivative of Downwash δε/δα trailing edge angle Angle Elevator-surface Chα moment derivative with respect to alpha [power] prop or jet but not Elevator-surface Chδ moment derivative due to both (no turboprop) Elevator deflection [prop] PROPELLER All above values ENGINE calculated using a
derivative SSPNE semispan exposed panel length Cnr Cy from Yaw Rate derivative SSPN theoretical semispan exposed panel length Cm_Total • Total Pitching Moment Coefficient due to: SAVSI inboard sweep angle Cmα Cm from Basic geometry CHSTAT reference chord station (0.25) Cmδf Cm from Flap deflection TWISTA twist angle Cmδe Cm from Elevator deflection DHDADI dihedral angle Cmq Cm from Pitch Rate derivative TYPE wing shape (1=straight tapered, 2=delta,3=cranked) Cmαdot Cm from Angle of Attack Rate derivative Cl_Total • Total Rolling Moment Coefficient due to: [Aileron, Wing Flaps, and Elevators] Clδa Cl from Aileron Deflection NDELTA # of deflectionangles to test Clβ Cl from Sideslip DELTA specific deflection angles Clp Cl from Roll Rate derivative SPANFI dimension of flap Clr Cl from Yaw Rate derivative SPANFO Cn_Total • Total Yawing Moment Coefficient CHRDFI (Cyδa) Cn from Aileron deflection CHRDFO (Cyβ) Cn from Sideslip NTYPE nose type (1=round, 2=elliptical, 3=sharp) v(Cyp) Cn from Roll Rate derivative CB average balance chord (Cyr) Cn from Yaw Rate derivative TC average thickness • Misc PHETE tangent of arifoil trailing edge angle ε Horizontal Tail Downwash Angle PHETEP tangent of arifoil trailing edge angle δε/δα Derivative of Downwash Angle Chα Elevator-surface derivative with respect to alpha [power] prop or jet but not both (no turboprop) Chδ Elevator-surface derivative due to Elevator deflection [prop] PROPELLER ENGINE All above values calculated using a moment moment
FDL%20SD2%20Paper.docx