What is it about?
The interference of an impinging plane oblique shock wave with the viscous shock layer on a cylinder has been studied numerically for rarefied-gas flow regime. The calculations have been performed within the framework of the direct simulation Monte-Carlo technique [1] and the Navier-Stokes equations for a perfect gas using the shock capturing method [2]. The principal properties of flow parameters have been studied for five different types of interference at low Reynolds numbers. The differences with respect to the previously investigated interference regimes for high Reynolds numbers have been examined.
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Why is it important?
It has been found that the local pressure and heat transfer coefficients on the surface of a cylinder may considerably (by a factor of 3.5) exceed the values on the edge stagnation line observed in the absence of interference. The type IV interference pattern observed in continuum flows has not been found in this study.
Perspectives
Advanced heat protection methods should be developed for protecting cylindrical edges of hypersonic vehicles and engines.
Vladimir Riabov
Rivier University
Read the Original
This page is a summary of: Shock/shock interference in hypersonic low-density flows near a cylinder, January 2019, American Institute of Physics,
DOI: 10.1063/1.5119598.
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