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 ∼1%.


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    Titel :

    Mach 10 Rayleigh Scattering Gas-Cap Density, Pressure, and Shock-Jump Measurements


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Lokalklassifikation TIB:    770/7040