Title

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

Date

1962

Index Abstract

Coming Soon

Photo Quality

Complete

Report Number

AEDC TDR 62-78

Creator

Rhodes, R. P.

Rubins, P. M.

Chriss, D. E.

Corporate Author

ARO, Inc.

Laboratory

Arnold Engineering Development Center

Extent

76

Identifier

AD0275366

Access Rights

ASTIA

Distribution Classification

1

Contract

AF 40(600)-800

DoD Project

6952

DoD Task

695201

DTIC Record Exists

No

Distribution Change Authority Correspondence

AEDC USAE LTR

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.

The abstract for this report is either unavailable or has yet to be entered

Report Availability

Full text available

Date Issued

1962-05

Publisher

Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force

Provenance

IIT

Type

report

Format

1 online resource