• DocumentCode
    2837141
  • Title

    Application of pulse tube for the test of the engines of hypersonic aircraft

  • Author

    Latypov, A.F. ; Yaroslavtsev, M.I. ; Zudov, V.N.

  • Author_Institution
    Inst. of Theor. & Appl. Mech., Acad. of Sci., Novosibirsk
  • fYear
    1995
  • fDate
    18-21 Jul 1995
  • Abstract
    At MH=10, 12.2; TOH=2400 K, POH=300-400 MPa in the hot-short aerodynamic tunnel, investigations of operating processes in the engine path of the scramjet model were performed. The model has rather simple external configuration. The inner channels are those ones which allow the burning of gaseous hydrogen as in sub- and super-sonic flows. Quantitative data on the distribution of pressure in the engine path were obtained. The experiments were performed in the IT-302M wind tunnel
  • Keywords
    aerospace engines; aerospace simulation; aircraft testing; shock tubes; shock waves; wind tunnels; 2400 K; 300 to 400 MPa; distribution of pressure; engine path; engine testing; hot-short aerodynamic tunnel; hypersonic aircraft engines; inner channels; pulse tube; scramjet model; Aircraft propulsion; Automatic testing; Chemicals; Engines;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Instrumentation in Aerospace Simulation Facilities, 1995. ICIASF '95 Record., International Congress on
  • Conference_Location
    Wright-Patterson AFB, OH
  • Print_ISBN
    0-7803-2088-3
  • Type

    conf

  • DOI
    10.1109/ICIASF.1995.519482
  • Filename
    519482
    • Link To Document
    https://search.isc.ac/dl/search/defaultta.aspx?DTC=49&DC=2837141