Experimental Study of the Longitudinal Hypersonic Corner Flow Field Hermes-R&D Research Program, Problem No. 5

  • A. Henckels
  • F. Maurer
Conference paper


Recent project activities for reentry vehicles provided an impetus to numerical and experimental studies of hypersonic flows with inviscid-viscous interaction phenomena like separation-induced vortex flows. The kinetic surface heating, which is one of the major design problems of such vehicles, is for instance strongly influenced by the existence and intensity of vortices as well as the location and type of separation and reattachment of hypersonic boundary layers.

Previous experimental investigations of longitudinal corner flows were mostly restricted to a streamwise compression corner, while in the present study a wind tunnel corner flow model has been tested exemplaryly for the case that at least one of the two plates forming the corner is at high incidence up to 20 degrees simulating lee-side flow situation. The free stream Mach number is 8.7. For measuring heat flux values an infra-red thermovision camera system in connection with modern image processing allows thermal mapping of the surface heat load distribution. In addition to the thermographic results the flow interpretation was supported by an oil flow visualisation study. The received quantitative results may be helpful to validate numerical codes.


Wind Tunnel Hypersonic Flow Lead Edge Vortex Local Heat Transfer Coefficient Stanton Number 
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  1. [1]
    Boylan, D. E.; Carver, D. B.; Stallings, D. W.; Trimmer, L. L.: Measurement and Mapping of Aerodynamic Heating Using a Remote Infrared Scanning Camera in Conti nous Flow Wind Tunnels, AIAA Paper No. 78–799, pp. 213, 1978Google Scholar
  2. [2]
    Henckels, A.; Maurer, F.: Applications of Infrared-Thermography in a Hypersonic Blow Down Wind Tunnel, 13th International Congress on Instrumentation in Aerospace Simulation Facilities (ICIASF ’89 Record), pp. 516–524, Göttingen, September 18–21, 1989Google Scholar
  3. [3]
    Heyser, A.; Pfeiffer, H.; Schepers, H.-J.: Der Hyperschallwindkanal H2 der DFVLR in Porz-Wahn, Jahrbuch Landesamt für Forschung NRW, 1969Google Scholar
  4. [4]
    Korkegi, R. H. On the structure of Three-Dimensional Shock-Induced Separated Flow Regions AIAA Journal Vol. 14, No. 5, pp. 597, May 1976Google Scholar
  5. [5]
    Peake, D., J.; Tobak, M.: Three-Dimensional Interactions and Vortical Flows with Emphasis on High Speeds, AGARDograph No. 252, edited by R. H. Korkegi, 1980Google Scholar
  6. [6]
    Schepers, H.-J.: Ausbildung des Strömungsfeldes in längsangeströmten Ecken und Auswirkungen auf stromabwärts angeortnete Klappen bei Hyperschallanströmung, DFVLR-FB 78–23, 1978Google Scholar
  7. [7]
    Stainback, P. C.; Weinstein, L. M.: Aerodynamic Heating in the Vicinity of Corners at Hypersonic Speeds, NASA Technical Note D-4130, November 1967Google Scholar
  8. [8]
    Watson, R. D.; Weinstein, L. M.: A Study of Hypersonic Corner Flow Interactions, AIAA Paper No. 70–227, 1970 1980Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1991

Authors and Affiliations

  • A. Henckels
    • 1
  • F. Maurer
    • 1
  1. 1.Hauptabteilung Windkanäle Abteilung WT-WKDLRKöln-PorzGermany

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