The effect of exhaust plume/afterbody interaction on installed scramjet performance
The effect of exhaust plume/afterbody interaction on installed scramjet performance
- New search for: Edwards, T.
- New search for: Edwards, T.
An upwind, implicit Navier-Stokes computer program has been applied to hypersonic exhaust plume/afterbody flow fields. The capability to solve entire vehicle geometries at hypersonic speeds, including an interacting exhaust plume, has been demonstrated on a simplified nozzle/afterbody model, as well as a generic hypersonic vehicle. Comparison of the numerical results with available experimental data shows good agreement in all cases investigated. For moderately underexpanded jets, afterbody forces were found to vary linearly with the nozzle exit pressure. Coupling a species continuity equation to the Navier-Stokes equations enabled calculations indicating that exhaust gases with low isentropic exponents gamma contribute up to 25 % more force than high-gamma-exhaust gases. The nozzle geometry was found also to be important to extracting thrust from the exhaust plume. Highly underexpanded jets created a strong plume shock, and the interaction of this shock with the afterbody was found to produce a complicted pattern of crossflow separation.
Document information
The effect of exhaust plume/afterbody interaction on installed scramjet performance
Einfluss der Abgasfahne/Triebwerk-Wechselwirkung auf die nominelle Raketenleistung
AIAA-Papers ; Jan ; 1-17
1988
17 Seiten, 20 Bilder, 35 Quellen
Conference paper
English