Hypersonic Transitional Flow in a Compression Corner in 2D Configuration

  • A. Chpoun
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)


Compression corner problems were widely investigated in the past three decades in both laminar and turbulent cases. The basic phenomena and the main flow features on such configurations are now well known. However, the prediction of the severe aerothermodynamic loads which follow from the laminar-turbulent transition induced by the interaction process remains of considerable pratical importance. Thus, in this case, it is of interest to gather extensive new data. In Europe, associated with the HERMES spacecraft program, this problem has ben raising a new interest for a few years. The present study has been carried out within the framework of the current european hypersonic research program.


Reynolds Number Wall Pressure Separation Region Hinge Line Heat Transfer Measurement 
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  1. 1.
    Needham, D.A.; Stollery, J.L.; “Boundary Layer Separation in Hypersonic Flows,” AIAA Paper n° 66–455, June 1966.Google Scholar
  2. 2.
    Hill, W.G.; “A Comparaison of Theory and Experiment for Laminar Separation ahead of a Compression Corner at Supersonic and Low Hypersonic Speeds,” Grumman Research Department Report RE-401, Dec. 1970, p. 27.Google Scholar
  3. 3.
    Holden, M.S.; “Boundary-Layer Displacement and Leading Edge Bluntness Effects on Attached and Separated Laminar Boundary Layers in a Compression Corner. Part 1: Theoritical Study,” AIAA Journal, 8, 12, Dec.1970.CrossRefGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1990

Authors and Affiliations

  • A. Chpoun
    • 1
  1. 1.Laboratoire d’AérothermiqueCentre National de la Recherche ScientifiqueMeudonFrance

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