Comparison between computational and experimental data for a hypersonic laser propelled vehicleA 3-D axisymmetric hypersonic engine inlet was investigated using PARC2D, an ideal gas Computational Fluid Dynamics code. The code was used to predict the results of tests conducted in the Rensselaer Polytechnic Institute Hypersonic Shock Tunnel which measured surface and pitot pressures, and shock positions (through Schlieren photography) at freestream Mach numbers of 10, 13, and 15. A strong viscous/shock interaction was observed in both the experiment and the CFD results, due to the model's parabolic compression ramp. Good agreement was found between the experimental results and the CFD solution both for surface pressures and shock positions. Agreement between pitot pressures was less reliable.
Document ID
19920071555
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Messitt, D. G. (NASA Headquarters Washington, DC United States)
Dallemagne, P. C. (NASA Headquarters Washington, DC United States)
Myrabo, L. N. (NASA Headquarters Washington, DC United States)
Nagamatsu, H. T. (Rensselaer Polytechnic Institute, Troy, NY, United States)