Experimental Study of the Longitudinal Hypersonic Corner Flow Field Hermes-R&D Research Program, Problem No. 5
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.
KeywordsWind Tunnel Hypersonic Flow Lead Edge Vortex Local Heat Transfer Coefficient Stanton Number
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