Contrails
The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

The Effect Of Heat Release On The Flow Parameters In Shock-Induced Combustion

Report Number: AEDC TDR 62-78
Author: Rhodes, R. P.
Author: Rubins, P. M.
Author: Chriss, D. E.
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-05
Pages: 76
Contract: AF 40(600)-800
Project: 6952
Task: 695201
AD Number: AD0275366

Abstract:
Experimental investigations were conducted in a Mach 3 combustion tunnel to detemine heat release characteristics of a hydrogen-air mixture after it had passed through a normal shock. Inlet temperature varied from 1800 to 3000 degrees R. Heat relsease was indicated by three types of measurements: 1. Combustion and total temperature rise calculated from gas analysis. 2. Total pressure loss caused by heat addition. 3. Ultra-violet emmission at the OH emission frequencies, indicating an H2-O2 reaction. Combustion efficiency was found to increase with temperature and to be independent of fuel-air ratio. Fuel passing through an oblique shock was observed to emit a radiation similar to that observed from the normal shock combustion.


Provenance:
IIT
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