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Prikladnaya Mekhanika i Tekhnicheskaya Fizika, 2000, Volume 41, Issue 1, Pages 50–56
(Mi pmtf2869)
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This article is cited in 7 scientific papers (total in 7 papers)
Experimental study of evolution of disturbances in a supersonic boundary layer on a swept-wing model under controlled conditions
A. D. Kosinov, N. V. Semenov, Yu. G. Ermolaev, V. Ya. Levchenko Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk 630090
Abstract:
Experimental data on stability of a three-dimensional supersonic boundary layer on a swept wing are presented. Evolution of artificial wave trains was studied. The experiments were conducted for Mach number $\mathrm{M}=2.0$ and unit Reynolds number $\mathrm{Re}_1=6.6\cdot10^6$ m$^{-1}$ on a swept-wing model with a lenticular profile and a $40^\circ$ sweep angle of the leading edge at zero incidence. Excitation of high-frequency disturbances caused by secondary-flow instability at a high initial amplitude was observed. It is shown that the evolution of disturbances at frequencies of $10$, $20$, and $30$ kHz is similar to the development of travelling waves for the case of subsonic velocities.
Received: 30.11.1998
Citation:
A. D. Kosinov, N. V. Semenov, Yu. G. Ermolaev, V. Ya. Levchenko, “Experimental study of evolution of disturbances in a supersonic boundary layer on a swept-wing model under controlled conditions”, Prikl. Mekh. Tekh. Fiz., 41:1 (2000), 50–56; J. Appl. Mech. Tech. Phys., 41:1 (2000), 44–49
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https://www.mathnet.ru/eng/pmtf2869 https://www.mathnet.ru/eng/pmtf/v41/i1/p50
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