Hypersonic Transitional Flow in a Compression Corner in 2D Configuration
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.
KeywordsReynolds Number Wall Pressure Separation Region Hinge Line Heat Transfer Measurement
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