Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows

摘要: †Discrepancies between experiment and computation for shuttle leeside flow separation, which came to light in the Columbia accident investigation, are resolved. Tests were run Langley Research Center 20-Inch Hypersonic CF 4 Tunnel with a baseline orbiter model two extended trailing edge models. The edges altered wing separation lines, moving lines toward fuselage, proving that modeling does affect flow. Computations then made wake grid. These calculations more closely matched experiments. Thus, present findings demonstrate it is imperative include domain CFD order accurately predict hypersonic vehicles at high angles of attack.