Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You or Your Team.

Learn More →

The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge

The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable... The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge

Loading next page...
 
/lp/springer-journals/the-impact-of-weak-shock-waves-on-the-flow-in-the-boundary-layer-of-a-5UdkEssMhh

References (14)

Publisher
Springer Journals
Copyright
Copyright © V.L. Kocharin, A.D. Kosinov, A.A. Yatskikh, Yu.G. Ermolaev, N.V. Semionov, M.V. Piterimova, S.G. Shevelkov, and O.P. Minin 2019
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/S0869864319060027
Publisher site
See Article on Publisher Site

Abstract

The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Nov 27, 2019

There are no references for this article.