An experimental and numerical study has been performed of the flow physics occurring in the Naval Surface Warfare Center Hypervelocity Wind Tunnel No.9 Mach 14 Nozzle. Mach 8, 10, 14, and 18 test section conditions are obtained utilizing various axisymmetric contoured wind tunnel nozzles. Numerical and experimental results are presented for the Mach 14 configuration.
A comparison of experimental data with CFD for the NSWC Hypervelocity Wind Tunnel No. 9 Mach 14 Nozzle
1992-07-01
Conference paper
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English