The Effect Of Heat Release On The Flow Parameters In Shock-Induced Combustion
Report Number: AEDC TDR 62-78
Author(s): Rhodes, R. P., Rubins, P. M., Chriss, D. E.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-05
Pages: 76
Contract: AF 40(600)-800
DoD Project: 6952
DoD Task: 695201
Identifier: 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
Author(s): Rhodes, R. P., Rubins, P. M., Chriss, D. E.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-05
Pages: 76
Contract: AF 40(600)-800
DoD Project: 6952
DoD Task: 695201
Identifier: 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