Abstract
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.
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References
Needham, D.A.; Stollery, J.L.; “Boundary Layer Separation in Hypersonic Flows,” AIAA Paper n° 66–455, June 1966.
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.
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.
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© 1990 Springer-Verlag Berlin Heidelberg
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Chpoun, A. (1990). Hypersonic Transitional Flow in a Compression Corner in 2D Configuration. In: Arnal, D., Michel, R. (eds) Laminar-Turbulent Transition. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-84103-3_48
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DOI: https://doi.org/10.1007/978-3-642-84103-3_48
Publisher Name: Springer, Berlin, Heidelberg
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