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Hypersonic Viscous Flows

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Modern Developments in Gas Dynamics

Abstract

At hypersonic Mach numbers, significant pressures are induced on aerodynamic surfaces by both viscosity and bluntness effects. Viscosity-induced pressures are caused by the growth of the boundary layer. They are accounted for in the manner proposed by Prandtl (1) many years ago when he suggested taking the computed boundary-layer displacement thickness as the boundary of a new body for which the external flow is then calculated. Bluntness-induced pressures result from complicated flow field interactions integral with the highly-curved nose shock and attendant strong entropy and vorticity gradients associated with blunt noses in hypersonic flow; this interaction is essentially inviscid.

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  1. Flow Analysis Section, NASA—Langley Research Center, USA

    Arthur Henderson Jr. (Head)

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  1. Science and Technology Space Division, North American Rockwell Corporation, Downey, California, USA

    W. H. T. Loh (Manager) (Manager)

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Henderson, A. (1969). Hypersonic Viscous Flows. In: Loh, W.H.T. (eds) Modern Developments in Gas Dynamics. Springer, Boston, MA. https://doi.org/10.1007/978-1-4615-8624-1_3

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