A major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the development of an earopropulsion system capable of withstanding the sustained high thermal loads expected during hypersonic flight. Three aerothermal load related concerns are the boundary layer transition from laminar to turbulent flow, articulating panel seals in high temperature environments, and strut (or cowl) leading edges with shock-on-shock interactions. A multi-disciplinary approach is required to address these technical concerns. A hydrogen/oxygen rocket engine heat source has been developed at the NASA Lewis Research Center as one element in a series of facilities at national laboratories designed to experimentally evaluate the heat transfer and structural response of the strut (or cowl) leading edge. A recent experimental program conducted in this facility is discussed and related to cooling technology capability. The specific objective of the experiment discussed is to evaluate the erosion and oxidation characteristics of a coating on a cowl leading edge (or strut leading edge) in a supersonic, high heat flux environment. Heat transfer analyses of a similar leading edge concept cooled with gaseous hydrogen is included to demonstrate the complexity of the problem resulting from plastic deformation of the structure. Macro-photographic data from a coated leading edge model show progressive degradation over several thermal cycles at aerothermal conditions representative of high Mach number flight.
Hypersonic engine leading edge experiments in a high heat flux, supersonic flow environment
Versuche an der Eintrittskante eines Hyperschalltriebwerkes in einer Überschallströmung mit hohem Wärmefluß
1994
10 Seiten, 10 Bilder, 9 Quellen
Conference paper
English
Blunt-leading-edge problem in hypersonic flow
Engineering Index Backfile | 1963
|THE BLUNT-LEADING-EDGE PROBLEM IN HYPERSONIC FLOW
AIAA | 1963
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