Algebraic Prediction of Pressure and Lift for High-Angle of Attack Supersonic Asymmetric Delta Wings Based on Geometric Similarity

In this paper, we explore the feasibility of deriving a simple, physically meaningful, andcompact formulation for the pressure distribution and lift of an asymmetric delta wing athigh angles of attack with an attached shock wave. Such a model would be valuable forrapid engineering analysis. Our approach begins with a compact pressure approximationin the linear regime, which is then extended to the nonlinear case through a geometrictransformation and the assumption of functional similarity between linear and nonlinearsolutions. This method bridges the solution in the central nonuniform flow region tothe exact solutions in the uniform flow regions near the leading-edge shock waves , in amanner analogous to methods used for supersonic starting flow. The model is shown to reproduce existing results for both symmetric and yawed delta wings within an acceptable error margin, providing a compact explicit expression for the normal force coefficient as a weighted average of pressure coefficients from the two uniform flow regions. Additionally, weoutline how the approach may be extended to the upper surface, where the uniform flowis described by swept Prandtl-Meyer relations.