The influence of flow non-uniformities in air-breathing hypersonic propulsion systems
The influence of flow non-uniformities in air-breathing hypersonic propulsion systems
- Neue Suche nach: Lewis, M.J.
- Neue Suche nach: Hastings, D.E.
- Neue Suche nach: Lewis, M.J.
- Neue Suche nach: Hastings, D.E.
The generation of inlet non-uniformities and their influence on the flowfield of a supersonic combustion ramjet, or scramjet, is examined. In particular, the problem of inlet Mach number and mass flux stratification through the formation of a thick forebody boundary layer is considered, along with the effect that the boundary layer flow will have on the inviscid core region inside the scramjet. Estimates are made of the expected thickness of the hypersonic boundary layer at various flight conditions that are applicable to a trans-atmospheric vehicle trajectory, and these are related to the position of the vehicle bow shock. It is found that an engine designed for uniform flow cannot tolerate large inlet gradients in Mach number and mass flux. It is suggested that, in order to reduce the thickness of the forebody boundary layer, and aerospace plane may operate more effectively at lower altitudes that those which optimize lift-to-drag. Such a vehicle would also be restricted to a narrow range of angles of attack because of the sensitivity of the hypersonic boundary layer thickness to deflection angle.
Dokumentinformationen
The influence of flow non-uniformities in air-breathing hypersonic propulsion systems
Der Einfluss von Stroemungsungleichmaessigkeiten in Hyperschallantriebssystemen mit Luftansaugung
AIAA-Papers ; Jul ; 1-14
1987
14 Seiten, 22 Bilder, 2 Tabellen, 15 Quellen
Aufsatz (Konferenz)
Englisch
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