Pressure and heat transfer investigation of a modified NASP baseline configuration at M = 6A cooperative NASA Langley-Boeing investigation was conducted in the Langley eight-Foot High Temperature Tunnel to obtain hypersonic pressure and heat transfer data. In this investigation a large scale (1/20), modified version of the National Aero-Space Plane configuration known as the 'Government Baseline' was tested at a nominal Mach number of 6; at two Reynolds numbers (0.6 and 1.6 million per foot); and at angles of attack from about 0 to 15 deg. There were several purposes for the investigation: to provide a windward and leeward pressure and heat transfer data base for a realistic configuration for verification of computational methods, to provide these data for a large-scale model, and to provide these data for true temperature conditions because of concern about data from low temperature tunnels.
Document ID
19890037837
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reubush, David E. (NASA Langley Research Center Hampton, VA, United States)
Omar, M. Emmett (Boeing Advanced Systems Seattle, WA, United States)