Effect of Heat Release on Flow Parameters in Shock Induced Combustion 640008

Experimental investigations were conducted in a Mach 3 combustion tunnel to determine the characteristics of heat release of a hydrogen-air mixture after it passed through a normal shock. Inlet temperature was varied from 1800-3000 R. Heat release was indicated by the H2 reaction and total temperature rise calculated from gas analysis and total pressure loss caused by heat addition.
H2 reaction was found to increase with temperature and to be independent of fuel-air ratio.


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