Abstract
A blunt nose flare model was designed and constructed and is to be tested in the Langley Mach 6 quiet tunnel. The experiment is designed to investigate the effects of roughness and pressure gradient on hypersonic boundary layer transition. The design of the model is discussed, as are several new experimental techniques which are to be incorporated. Inviscid boundary layer, and stability computations are reported at both Mach 6 and Mach 3.5. Some preliminary experimental results at Mach 3.5 are also given.
This author acknowledges assistance with the development of the hot film wall shear sensors, from the NASA Langley Instrument Research Division under grant NAG-1–1201.
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© 1992 Springer-Verlag New York, Inc.
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Schneider, S.P., Beckwith, I.E. (1992). High Speed Boundary Layer Transition on a Blunt Nose Flare with Roughness. In: Hussaini, M.Y., Kumar, A., Streett, C.L. (eds) Instability, Transition, and Turbulence. ICASE NASA LaRC Series. Springer, New York, NY. https://doi.org/10.1007/978-1-4612-2956-8_3
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DOI: https://doi.org/10.1007/978-1-4612-2956-8_3
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