Characteristics of Thin Triangular Wings With Constant-Chord Full-Span Control Surfaces at Supersonic Speeds

摘要

A theoretical analysis was made of the characteristics of constant- chord full-span control surfaces on thin triangular wings at supersonic speed by use of methods based on the linearized equation for supersonic flow. Expressions were found for the lift effectiveness, pitching-moment coefficient, hinge-moment coefficient due to control deflection, and hinge-moment coefficient due to angle of attack. These expressions were given as functions of the ratio of flap chord to wing chord and the ratio of the tangent of the wing-semiapex angle to the tangent of the Mach angle.