The Method of Heat Flux Simulating in Hypersonic Aerothermodynamics

A new method is offered to simulate heat transfer processes in nonequilibrium viscous shock layers near the catalytic body surface at hypcrsonic wind tunnel and free natural flight conditions. The method is based on computations of nonequilibrium parameters in thin viscous sbock layers, and on an analogy with flows that arise behind normal shock waves. The obtained simplified relationships between the linear scales of the vehicle and the model, velocities of the flows and their densities determine the similar structures of the viscous layers and heat fluxes at hypersonic wind tunnel and flight conditions. Nomenclature