A new similarity law for transonic–supersonic flow

How to determine accurately and efficiently the aerodynamic forces of aircraft in high-speed flow is one great challenges modern aerodynamics. In this Letter we propose a new similarity law for steady transonic-supersonic over thin bodies. The based on local Mach number frozen principle. It depends both specific heat ratio free-stream number. enables lift drag coefficients from that reference state which more reachable. validity has been confirmed by excellent agreement with numerical simulations two-dimensional airfoil flows three-dimensional wing flows.