Analytical and experimental investigations of the oblique detonation wave engine conceptWave 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 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 Computational Fluid Dynamics (CFD) codes which fully couple finite rate chemistry with fluid dynamics. In addition, experimental proof-of-concept studies are being performed in an arc heated hypersonic wind tunnel. Several fuel injection design 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.
Document ID
19910013856
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Menees, Gene P. (NASA Ames Research Center Moffett Field, CA., United States)
Adelman, Henry G. (NASA Ames Research Center Moffett Field, CA., United States)
Cambier, Jean-Luc (Eloret Corp. Moffett Field, CA., United States)