Email RIS file
Bookmark
Report an Issue

Analytical and experimental investigations of the oblique detonation wave engine concept

Author
Cambier, Jean-Luc
Published
Feb 1, 1991.
Physical Description
1 electronic document
Additional Creators
Adelman, Henry G. and Menees, Gene P.
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Wave combustors, which include the Oblique Detonation Wave Engine (ODWE), are attractive propulsion concepts for hypersonic flight. These engines utilize oblique shock or detonation waves to rapidly mix, ignite, and combust the air-fuel mixture in thin zones in the combustion chamber. Benefits of these combustion systems include shorter and lighter engines which will require less cooling and can provide thrust at higher Mach numbers than conventional scramjets. The wave combustor's ability to operate at lower combustor inlet pressures may allow the vehicle to operate at lower dynamic pressures which could lessen the heating loads on the airframe. The research program at NASA-Ames includes analytical studies of the ODWE combustor using CFD codes which fully couple finite rate chemistry with fluid dynamics. In addition, experimental proof-of-concept studies are being carried out in an arc heated hypersonic wind tunnel. Several fuel injection designs were studied analytically and experimentally. In-stream strut fuel injectors were chosen to provide good mixing with minimal stagnation pressure losses. Measurements of flow field properties behind the oblique wave are compared to analytical predictions.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19930023185.
Accession ID: 93N32374.
NAS 1.15:102839.
NASA-TM-102839.
A-90195.
AGARD PEP 75th Symposium; 28 May - 1 Jun. 1990; Madrid; Spain.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15666899