Book Description
The present paper makes use of and extends a paper by Munk in which simple dynamic concepts are used to prove that the lift-curve slope and thickness drag of supersonic airfoils or system of airfoils with supersonic edges are the same when the airfoil is flown in a reversed direction. This extension of Munk's work provides a proof that the thickness drag, lift-curve slope, damping in roll, and the damping-in-pitch parameter remain the same when any airfoil is reversed, in both subsonic and supersonic flow. The theorem applies to cases in which the trailing-edge velocities are finite; no restrictions are placed on plan form.
