Supersonic retropropulsion was experimentally examined in the Ames Research Center 9x7-Foot Supersonic Wind Tunnel at Mach 1.8 and 2.4. The experimental model, previously designed for and tested in the Langley Research Center Unitary Plan Wind Tunnel at Mach 2.4, 3.5 and 4.6, was a 5-in diameter 70-deg sphere-cone forebody with a 9.55-in long cylindrical aftbody. The forebody was designed to accommodate up to four 4:1 area ratio nozzles, one on the model centerline and the other three on the half radius spaced 120-deg apart. Surface pressure and flow visualization were the primary measurements, including high-speed data to investigate the dynamics of the interactions between the bow and nozzle shocks. Three blowing configurations were tested with thrust coefficients up to 10 and angles of attack up to 20-deg. Preliminary results and observations from the test are provided


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel


    Contributors:

    Conference:

    42nd AIAA Fluid Dynamics Conference and Exhibit ; 2012 ; New Orleans, LA, United States


    Publication date :

    2012-06-25


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Supersonic Retropropulsion Experimental Results from NASA Ames 9 × 7 Foot Supersonic Wind Tunnel

    Berry, Scott A. / Rhode, Matthew N. / Edquist, Karl T. | AIAA | 2014



    SUPERSONIC RETROPROPULSION EXPERIMENTAL RESULTS FROM THE NASA AMES 9-X 7-FOOT SUPERSONIC WIND TUNNEL

    Berry, S. / Rhode, M. / Edquist, K. et al. | British Library Conference Proceedings | 2012


    Supersonic Retropropulsion Experimental Results from the NASA Langley Unitary Plan Wind Tunnel

    Berry, Scott A. / Rhode, Matthew N. / Edquist, Karl T. et al. | NTRS | 2011