caa a22 4500 475775384 CHVBK 20180406123630.0 cr unu---uuuuu 170329e20000101xx s 000 0 eng 10.1007/BF02465235 doi (NATIONALLICENCE)springer-10.1007/BF02465235 Experimental study of evolution of disturbances in a supersonic boundary layer on a swept-wing model under controlled conditions [Elektronische Daten] [A. Kosinov, N. Semionov, Yu. Ermolaev, V. Levchenko] 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 numberM=2.0 and unit Reynolds numberRe 1=6.6·106m−1 on a swept-wing model with a lenticular profile and a40° 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 of10, 20, and30 kHz is similar to the development of travelling waves for the case of subsonic velocities. Kluwer Academic/Plenum Publishers, 2000 Kosinov A. aut Semionov N. aut Ermolaev Yu aut Levchenko V. aut Journal of Applied Mechanics and Technical Physics Kluwer Academic Publishers-Plenum Publishers 41/1(2000-01-01), 44-49 0021-8944 41:1<44 2000 41 10808 https://doi.org/10.1007/BF02465235 text/html Onlinezugriff via DOI 1 research-article jats NATIONALLICENCE 856 40 https://doi.org/10.1007/BF02465235 text/html Onlinezugriff via DOI NATIONALLICENCE 700 1- Kosinov A. aut NATIONALLICENCE 700 1- Semionov N. aut NATIONALLICENCE 700 1- Ermolaev Yu aut NATIONALLICENCE 700 1- Levchenko V. aut NATIONALLICENCE 773 0- Journal of Applied Mechanics and Technical Physics Kluwer Academic Publishers-Plenum Publishers 41/1(2000-01-01), 44-49 0021-8944 41:1<44 2000 41 10808 Metadata rights reserved Springer special CC-BY-NC licence nationallicence BK010053 XK010053 XK010000 NATIONALLICENCE NATIONALLICENCE NL-springer