Last edited by Arashira
Saturday, April 18, 2020 | History

4 edition of Shock tunnel studies of scramjet phenomena found in the catalog.

Shock tunnel studies of scramjet phenomena

Shock tunnel studies of scramjet phenomena

final technical report, NAGW-674.

by

  • 42 Want to read
  • 18 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Shock tunnels,
  • Data acquisition,
  • Enthalpy,
  • Mach number,
  • Supersonic combustion ramjet engines,
  • Hypersonic nozzles,
  • Investigation,
  • Thrust

  • Edition Notes

    Series[NASA contractor report] -- NASA-CR-203578., NASA contractor report -- NASA CR-203578.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17837869M
    OCLC/WorldCa40691816


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Shock tunnel studies of scramjet phenomena Download PDF EPUB FB2

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A shock tunnel investigation of a scramjet with a rectangular-to-elliptical shape transition (REST) inlet and an elliptical combustor has been conducted at conditions simulating flight at Mach Shock tubes and shock tunnel are used to simulate re-entry, but the duration of a shock tunnel test is extremely short.

In order to apply TSP to high. Among other things, one of the changes was provisions for a dummy scramjet to test if wind tunnel testing was correct. Unfortunately, on the final flight of the XA2 (flight ), the shock waves sent out by the scramjet at Mach caused extremely intense heating of.

Format: Book, Microform, Online; 1 v. National Library of Australia. Login | Register. Catalogue. Search the catalogue for collection items held by the National Library of Australia. New Shock tunnel studies of scramjet phenomena [microform]: supplement 10. Morgan has written: 'Shock tunnel studies of scramjet phenomena ' -- subject(s): Orbital velocity, Skin friction, Combustible flow, Subsonic.

Abstract. The Laboratory for Hypersonic and Shock wave Research (LHSR), Department of Aerospace Engineering, Indian Institute of Science (IISc), Bangalore is a dedicated centre for the research, among other domains of fluid dynamics, on Author: Rengarajan Sriram, Gopalan Jagadeesh.

Stalker RJ, Morgan RG, Paull A, Bresciani CP () Scramjet experiments in free piston shock tunnels. NASP Contractor Reportprinted by NASA Langley Google Scholar Swithenbank J, Eames I, Chin S, Ewan B, Yang Z, Cao J, Zhao X () Turbulent mixing in supersonic combustion : G.

Smeets. This proceedings present the results of the 29th International Symposium on Shock Waves (ISSW29) which was held in Madison, Wisconsin, U.S.A., from July 14 to J It was organized by the Wisconsin Shock Tube Laboratory, which is part of the College of Engineering of the University of.