Laser Rayleigh scattering measurements were performed along a 38.7 mm line in the gas cap created by a multipurpose crew vehicle model in the NASA Langley Research Center’s 31 in. Mach 10 air wind tunnel. Data were acquired at a fixed stagnation temperature near 990 K, and five stagnation pressures spanning 2.41 to 10.0 MPa (350–1454 psi). Data averaged over 371 images and 210 pixels per line produced measured gas-cap densities that agree with computed densities using the GASPROPS code within 1–5%. Gas-cap pressures calculated using measured offbody densities and computed gas-cap temperatures agree with onbody surface-pressure measurements within 5 to 15%. A line-averaged shock-density ratio of 5.92 based on four stagnation pressures agrees with the expected value of 5.97 to .
Mach 10 Rayleigh Scattering Gas-Cap Density, Pressure, and Shock-Jump Measurements
AIAA Journal ; 53 , 3 ; 756-762
2015-01-05
7 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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