Numerical Study on Combined Thermal Protection System on Hypersonic Vehicle and Structure Parameters Influence of Acoustic Cavity

Abstract

Hemispherical blunt model and numerical simulation method are used to investigate the thermal protection effects of combinational opposing jet and acoustic cavity concept with various structural parameters. Value conversion and solver selection are operated for more accurate simulation. The results illustrate that the shock wave structure has a negative relation with the height of cavity. Length-to- diameter ratio should be comprehensive considered when designing the nozzle of supersonic vehicles.