Delta Wing Drag due to Lift at Supersonic Speeds
 

This script calculates the lift induces drag properties of a three-dimensional wing arrow wing in potential flow. The planform geometry of the wing can be specified for cases of symmetric wing loading about the center-line.

Input Geometry Wing Span (m) Root Chord (m)   Leading Edge Sweep (deg) Stream Conditions Mach Number (M) Angle of Attack (deg)

AR = Mach No. LE = TE Sweep (Deg) = Mach No. TE =   CD/(βCL2) (0%) = CD/(βCL2) (100%) = CLalpha (per rad.) = CT/CL2 = kCD(0%) (1/CLα) = kCD0(100%) =   at CL = 0.10: CD(0%) (counts) = CD(100%) (counts) = ΔCD (counts) =   Xbar = (the number of root chords the aerodynamic center is behind the wing apex)   CL = CDi(0% LES) = CDi(100% LES) = Note: These are the drag due to lift values. The actual drag due to lift falls between the 0% and 100% leading edge suction values, and the wave and skin friction drag must be added to get total drag Ref: R.T. Jones and Doris Cohen, High Speed Wing Theory Princeton University Press, 1960, pp. 198-202.   Reynolds No. = Root Chord Skin Friction Coefficient = Wing Average Skin Friction Coefficient = Skin Friction Drag Coefficient, CDf=

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