Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review
Experimental study of the effects of couple weak waves on laminar-turbulent transition on attachment-line of a swept cylinder. / Yermolaev, Yu G.; Yatskih, A. A.; Kosinov, A. D. et al.
International Conference on the Methods of Aerophysical Research, ICMAR 2016: Proceedings of the 18th International Conference on the Methods of Aerophysical Research. ed. / Vasily Fomin. American Institute of Physics Inc., 2016. 120012 (AIP Conference Proceedings; Vol. 1770).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review
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TY - GEN
T1 - Experimental study of the effects of couple weak waves on laminar-turbulent transition on attachment-line of a swept cylinder
AU - Yermolaev, Yu G.
AU - Yatskih, A. A.
AU - Kosinov, A. D.
AU - Semionov, N. V.
AU - Kolosov, G. L.
AU - Panina, A. V.
PY - 2016/10/13
Y1 - 2016/10/13
N2 - An experiment on a swept cylinder with 68°-sweep angle at Mach number M = 2.5 is described. The flow attachment line was disturbed by two weak shock waves. Shock waves were generated by a two-dimensional surface inhomogeneity on the wall of the test section of wind tunnel. It was found that the laminar-turbulent transition on the attachment-line of the cylinder is accompanied by an uneven growth of pulsations. Influence of Mach waves on the transition when their fall on the cylinder far away from domain of measuring is not observed. The laminar-turbulent transition occurs at a much lower unit Reynolds numbers in the case when a pair of waves falling on the attachment-line near the measurement field.
AB - An experiment on a swept cylinder with 68°-sweep angle at Mach number M = 2.5 is described. The flow attachment line was disturbed by two weak shock waves. Shock waves were generated by a two-dimensional surface inhomogeneity on the wall of the test section of wind tunnel. It was found that the laminar-turbulent transition on the attachment-line of the cylinder is accompanied by an uneven growth of pulsations. Influence of Mach waves on the transition when their fall on the cylinder far away from domain of measuring is not observed. The laminar-turbulent transition occurs at a much lower unit Reynolds numbers in the case when a pair of waves falling on the attachment-line near the measurement field.
UR - http://www.scopus.com/inward/record.url?scp=84994067471&partnerID=8YFLogxK
U2 - 10.1063/1.4963935
DO - 10.1063/1.4963935
M3 - Conference contribution
AN - SCOPUS:84994067471
T3 - AIP Conference Proceedings
BT - International Conference on the Methods of Aerophysical Research, ICMAR 2016
A2 - Fomin, Vasily
PB - American Institute of Physics Inc.
T2 - 18th International Conference on the Methods of Aerophysical Research, ICMAR 2016
Y2 - 27 June 2016 through 3 July 2016
ER -
ID: 25838670