Effect of wall temperature in streamwise supersonic corner flow

The interaction between corner flow and heat transfer is very common in the internal external of hypersonic vehicle surface, but it not clear how wall thermal boundary condition affects supersonic layer. In present study, Reynolds stress model used to solve Reynolds-averaged Navier–Stokes equations. results show that when symmetrical temperature Tw less than or equal recovery Taw, mean velocity profile zone similar plate zone, higher zone. At heating Tw>Taw, both outer layer are different from near-wall distribution increases relatively, no longer law rises. Along spanwise wall, deviation velocity–temperature quadratic curve generalized analogy (GRA) relation within 10%. flow, under non-adiabatic satisfies GRA relation. effect on significant. It necessary consider analysis.