Turbulent heat-transfer measurements were made on transpiring flat plate model in Mach 8 tunnel using nitrogen, helium and argon as injection gases; model consisted of impermeable leading edge, transpiration section, and downstream section instrumented with asymptotic calorimeters; reduction in heat flux for transpiring section was obtained at higher blowing rates and Mach numbers than previously reported, whereas downstream heat flux results may be first quantitative measurements of their kind; reduction in turbulent heat flux to transpiring and downstream surfaces is found to be insensitive to Mach and Reynolds number, and transpiration gas.
Hypersonic turbulent transpiration cooling including downstream effects
AIAA J
AIAA Journal ; 4 , n 6
1966
7 pages
Article (Journal)
English
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Transpiration cooling in hypersonic flight
NTRS | 1989
|Transpiration Cooling in Hypersonic Flight
NTIS | 1989
|