The inflatable membrane reentry vehicle (IMRV) is one of the innovative aircrafts for next-generation space transport systems because of its reduced aerodynamic heating. In this study, a three-dimensional (3D) thermochemical nonequilibrium model is developed for simulating air plasma flows around an IMRV. This 3D nonequilibrium model includes the coupling of Navier–Stokes equations, 11 species, and 20 chemical reactions of air, a two-temperature model, and shear stress transfer k–ω turbulent transport equations. The simulated results are validated and compared with the corresponding experimental and numerical data published. Generally, they agree well with each other. It is concluded that the flight attack angle of the IMRV has an important impact on the flight stability. When the IMRV flies at an angle of attack of 0°, the translational-rotational and vibrational-electronic temperatures increase rapidly in the surge layer and decrease gradually near the wall. The wall pressure and heat flux decrease gradually along the capsule from the head to the inflatable film, increase rapidly where the inflatable film joins the rings, and decrease rapidly after the shoulder. The chemical and thermal nonequilibrium model developed in this study might be an accurate, stable, and low-cost modeling tool required for the optimal design of hypersonic reentry vehicles.
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