NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Experimental and analytical investigations of wave enhanced supersonic combustorsSupersonic combustion ramjet (scramjet) engines rely on rapid mixing and combustion of fuel for good performance. However, both of these processes are relatively slow compared to the residence times in supersonic combusters. Methods of improving the mixing process include subjecting the fuel streams to shock waves and the generation of vortices by spiriling, bifurcating struts. The combustion process can also be enhanced by shock or detonation waves. An oblique shock wave can act as a flameholder by increasing the pressure and temperature of the air-fuel mixture and thereby decreasing the ignition delay. If the oblique shock is sufficiently strong, then the combustion front and the shock wave can couple into a detonation wave. In this case, combustion occurs almost instantaneously in a thin zone behind the wave front. While the existence of standing oblique detonation waves has been proven in computer simulations, the experimental validation is still in progress. Currently, there is an experimental and analytical program at NASA-Ames Research Center to study detonations and other means of wave enhanced supersonic mixing and combustion.
Document ID
19950028573
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adelman, Henry G.
(Eloret Corp. Palo Alto, CA, United States)
Cambier, Jean-Luc
(Eloret Corp. Palo Alto, CA, United States)
Menees, Gene P.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
July 10, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-2787
Accession Number
95A60172
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available