The object of Cooperative Agreement NCC2-452 was to identify, develop, and document reliable turbulence models for incorporation into CFD codes, which would then subsequently be incorporated into numerical design procedures for the NASP and any other hypersonic vehicles. In a two-pronged effort, consisting of an experimental and a theoretical approach, several key features of flows over complex vehicles were identified, and test bodies were designed which were composed of simple geometric shapes over which these flow features were measured. The experiments were conducted in the 3.5' Hypersonic Wind Tunnel at NASA Ames Research Center, at nominal Mach numbers from 7 to 8.3 and Re/m from 4.9 x 10(exp 6) to 5.8 x 10(exp 6). Boundary layers approaching the interaction region were 2.5 to 3.7 cm thick. Surface and flow field measurements were conducted, and the initial boundary conditions were experimentally documented.
Hypersonic Flows as Related to the National Aerospace Plane
1995
24 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aerospace planes , Boundary layers , Computational fluid dynamics , Flow distribution , Flow measurement , Hypersonic flow , Hypersonic speed , Shock wave interaction , Turbulence models , Wind tunnel tests , Applications programs (Computers) , Boundary conditions , Boundary layer separation , Hypersonic vehicles , Hypersonic wind tunnels , Mach number , National aerospace plane program , Pressure effects , Reynolds number , Turbulent boundary layer
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