Delta Wing Drag due to Lift at Supersonic Speeds
This script calculates the lift induces drag properties of a three-dimensional wingarrow wing in potential flow. The planform geometry of the wing can bespecified 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
Angle of Attack