Static-temperature measurements performed in a reacting vitiated air-hydrogen Mach-2 flow in a duct in Test Cell 2 at NASA LaRC by using a coherent anti-Stokes Raman spectroscopy (CARS) system are discussed. The hypersonic propulsion Test Cell 2 hardware is outlined with emphasis on optical access ports and safety features in the design of the Test Cell. Such design considerations as vibration, noise, contamination from flow field or atmospheric-borne dust, unwanted laser- and electrically-induced combustion, and movement of the sampling volume in the flow are presented. The CARS system is described, and focus is placed on the principle and components of system-to-monochromator signal coupling. Contour plots of scramjet combustor static temperature in a reacting-flow region are presented for three stations, and it is noted that the measurements reveal such features in the flow as maximum temperature near the model wall in the region of the injector footprint.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    CARS temperature measurements in a hypersonic propulsion test facility


    Contributors:

    Publication date :

    1990-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    CARS TEMPERATURE MEASUREMENTS IN A HYPERSONIC PROPULSION TEST FACILITY

    Jarrett, O. / Smith, M. W. / Antcliff, R. R. et al. | British Library Conference Proceedings | 1990



    Hypersonic aerodynamics test facility using the external propulsion accelerator

    Rom, Joseph / Lewis, Mark / Gupta, Ashwani et al. | AIAA | 1995


    Facility requirements for hypersonic propulsion system testing

    Dunn, M.G. / Lordi, J.A. / Wittliff, C.E. et al. | Tema Archive | 1989


    Facility requirements for hypersonic propulsion system testing

    DUNN, M. / LORDI, J. / WITTLIFF, C. et al. | AIAA | 1989