Book Description
A theoretical analysis was made of characteristics of constant-chord partial-span control surfaces on thin triangular wings at supersonic speeds by use in methods based on linearized theory for supersonic flow. Two cases were treated: In one the flap extended outboard from the center of wing and in the other the flap extended inboard from wing tip. Expressions were found for lift coefficient, rolling-moment coefficient, and hinge-moment coefficient due to flap deflection, hinge-moment coefficient due to angle of attack, and pitching-moment coefficient due to flap lift. A few figures are given to illustrate application equations.
