Discrepancies between experiment and computation for shuttle leeside flow separation, which came to light in the Columbia accident investigation, are resolved. Tests were run in the Langley Research Center 20-Inch Hypersonic CF4 Tunnel with a baseline orbiter model and two extended trailing edge models. The extended trailing edges altered the wing leeside separation lines, moving the lines toward the fuselage, proving that wing trailing edge modeling does affect the orbiter leeside flow. Computations were then made with a wake grid. These calculations more closely matched baseline experiments. Thus, the present findings demonstrate that it is imperative to include the wake flow domain in CFD calculations in order to accurately predict leeside flow separation for hypersonic vehicles at high angles of attack.
Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows
2005
22 pages
Report
No indication
English
Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows
British Library Conference Proceedings | 2005
|Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows
British Library Conference Proceedings | 2005
|