Preliminary Study of Turbulence for a Lobed Body in Hypersonic Flight
Final rept. Oct 2011-Sep 2012
AIR FORCE RESEARCH LAB EGLIN AFB FL MUNITIONS DIRECTORATE
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The present study addresses the aerodynamics of a lobed body immersed in a Mach 6 hypersonic flow field at sea level. As a first study of this type, the shape of the body is held fixed, and the flow field is resolved by applying state-of-the-art large eddy simulation techniques in conjunction with a hybrid shock-turbulence capturing algorithm. Air is treated as a mixture of nitrogen and oxygen, and the governing equations are closed by a modern compressible turbulence closure term. Pressure is determined by using the thermally perfect gas equation of state applied to each species. The distribution of temperature is determined on the body surface as well as temperature gradients based upon adiabatic wall boundary conditions. The structure of the flow field is examined as is the time required for stationarity. Both turbulent statistics and spectra are determined at points on the surface of the body. Times series analyses are performed for aerodynamics forces encountered by the body.
- Military Aircraft Operations