Paper reports experimental investigation of film cooling in supersonic free stream flowing along flat plate; main flow consists of air at Mach number of 3.01; either air or helium was injected through tangential (stepdown) slot to act as secondary fluid; schlieren photographs are presented and adiabatic wall temperature measurements are described.
Film cooling with air and helium injection through rearward-facing slot into supersonic air flow
AIAA J
AIAA Journal ; 4 , n 6
1966
5 pages
Article (Journal)
English
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