Abstract
Direct numerical simulations of the evolution of disturbances in a viscous shock layer on a flat plate are performed for a free-stream Mach number M ∞ = 21 and Reynolds number Re L = 1.44 · 105. Unsteady Navier-Stokes equations are solved by a high-order shock-capturing scheme. Processes of receptivity and instability development in a shock layer excited by external acoustic waves are considered. Direct numerical simulations are demonstrated to agree well with results obtained by the locally parallel linear stability theory (with allowance for the shock-wave effect) and with experimental measurements in a hypersonic wind tunnel. Mechanisms of conversion of external disturbances to instability waves in a hypersonic shock layer are discussed.
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Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 48, No. 3, pp. 84–91, May–June, 2007.
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Maslov, A.A., Kudryavtsev, A.N., Mironov, S.G. et al. Numerical simulation of receptivity of a hypersonic boundary layer to acoustic disturbances. J Appl Mech Tech Phys 48, 368–374 (2007). https://doi.org/10.1007/s10808-007-0046-3
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DOI: https://doi.org/10.1007/s10808-007-0046-3