Experimental and computational surface and flow-field results for an all-body hypersonic aircraftThe objective of the present investigation is to establish a benchmark experimental data base for a generic hypersonic vehicle shape for validation and/or calibration of advanced computational fluid dynamics computer codes. This paper includes results from the comprehensive test program conducted in the NASA/Ames 3.5-foot Hypersonic Wind Tunnel for a generic all-body hypersonic aircraft model. Experimental and computational results on flow visualization, surface pressures, surface convective heat transfer, and pitot-pressure flow-field surveys are presented. Comparisons of the experimental results with computational results from an upwind parabolized Navier-Stokes code developed at Ames demonstrate the capabilities of this code.
Document ID
19900058838
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lockman, William K. (NASA Ames Research Center Moffett Field, CA, United States)
Lawrence, Scott L. (NASA Ames Research Center Moffett Field, CA, United States)
Cleary, Joseph W. (Eloret Institute Sunnyvale, CA, United States)