Hypersonic Strong Interaction Similarity Solutions for Flow Past a Very Slender Axisymmetric Body.

W. B. Bush

ResearchPublished 1968

The Navier-Stokes hypersonic strong-interaction theory is presented for the flow of a viscous, heat-conducting, compressible fluid past a very slender axisymmetric body, when the ratio of the radius of the body to the radial thickness of the viscous layer(s) (which the body produces and supports), goes to zero. It is assumed that the fluid is a perfect gas having constant specific heats, a constant Prandtl number of order unity, and viscosity coefficients varying as a power of the absolute temperature. Solutions are studied for the free-stream Mach number, the free-stream Reynolds number based on the body's axial length, and a modified strong-interaction parameter going to infinity. It is shown that when the viscosity-temperature exponent is less than one, four distinct layers span the region between the shock wave and the body. The self-similar leading approximations for the behavior of the flow in these four regions are analyzed, and it is found that an arbitrary body supports "3/4-power" viscous and shock layers. 48 pp. Refs. (Author)

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  • Copyright: RAND Corporation
  • Availability: Web Only
  • Year: 1968
  • Document Number: RM-5699-ARPA

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Bush, W. B., Hypersonic Strong Interaction Similarity Solutions for Flow Past a Very Slender Axisymmetric Body. Santa Monica, CA: RAND Corporation, 1968. https://www.rand.org/pubs/research_memoranda/RM5699.html.
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