Hypervelocity imperfect gas nozzle design with shared wave-elimination contour

A hypervelocity imperfect gas nozzle with a shared wave-elimination contour is designed by the residual correction method, allowing test Mach number to be varied changing throat contours. Owing effects, classical method of characteristics boundary layer does not produce uniform flow field, resulting in significant deviation from target number. In this work, computational fluid dynamics solver used as an independent module without being coupled optimization code, reducing design complexity. Designers can choose appropriate according specified physical consider effects. The 15 better eliminates waves and achieves much higher uniformity than method. On basis, dependence domain influence transonic solution are solved characteristics, replaceable rigorously aerodynamics theory. Quantitative evaluations show that nozzles have same level uniformity, achieving high quality at 13–15. evaluation results validate design's feasibility, supporting future construction tunnels.