[ A(x) = A_\textmax \cdot \frac4xL\left(1 - \fracxL\right)^3/2 ]
Lift coefficient in hypersonic regime (Newtonian theory): hypersonic vst mac
Hypersonic, Variable Sweep, Area Rule, Morphing Structures, Wave Drag, Multi-Regime Flight 1. Introduction Hypersonic vehicles (Mach > 5) typically sacrifice low-speed performance for high-speed efficiency. Fixed-wing designs suffer from severe wave drag at transonic and supersonic transitions, limiting operational flexibility. Conversely, variable-sweep wings (e.g., B-1, F-14) improve subsonic/supersonic transition but are not designed for hypersonic thermal and pressure loads. Additionally, the classic area rule — which dictates that aircraft cross-sectional area distribution should be smooth to reduce wave drag — is Mach-dependent, yet most airframes are static. limiting operational flexibility. Conversely
A. J. Morrow(^1), L. Chen(^2) (^1)Department of Aerospace Engineering, Stanford University (^2)Center for Hypersonics, University of Queensland variable-sweep wings (e.g.