Theoretical Method for Solution of Aerodynamic Forces on Thin Wings in Nonuniform Supersonic Stream with an Application to Tail Surfaces

摘要

A theoretical method for obtaining the aerodynamic forces acting on a thin wing in an irrotational nonuniform supersonic stream is presented. The method, based on linearized theory, consists of a three-component superposition. The lift and the moments induced by the nonuniformity depend only on the wing plan-form boundary and on the vertical perturbation velocity of the free stream at each point of the plan-form area. Expressions are provided that permit lift and moment solutions for arbitrary plan forms and velocity distributions. The method is applied to determine lift and moments acting on a rectangular tail surface due to a spanwise parabolic distribution of upwash. Lift and moments due to a linear upwash distribution are also evaluated.