Computational Modeling and Validation for Hypersonic InletsHypersonic inlet research activity at NASA is reviewed. The basis for the paper is the experimental tests performed with three inlets: the NASA Lewis Research Center Mach 5, the McDonnell Douglas Mach 12, and the NASA Langley Mach 18. Both three-dimensional PNS and NS codes have been used to compute the flow within the three inlets. Modeling assumptions in the codes involve the turbulence model, the nature of the boundary layer, shock wave-boundary layer interaction, and the flow spilled to the outside of the inlet. Use of the codes and the experimental data are helping to develop a clearer understanding of the inlet flow physics and to focus on the modeling improvements required in order to arrive at validated codes.
Document ID
19970009256
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Povinelli, Louis A. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
August 17, 2013
Publication Date
October 1, 1996
Publication Information
Publication: Aerothermodynamics and Propulsion Integration for Hypersonic Vehicles