Transition control of Mach 6.5 hypersonic flat plate boundary layer

An artificial disturbance is introduced into the boundary layer over a flat plate to investigate the effect on the transition process in the Mach 6.5 wind tunnel at Peking University. A linear stability theory (LST) is utilized to predict the evolution of the eigenmodes, and the frequency of the art...

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Bibliographic Details
Published in:Applied mathematics and mechanics 2019-02, Vol.40 (2), p.283-292
Main Authors: Zhang, Yunchi, Li, Chi
Format: Article
Language:English
Subjects:
Applications of Mathematics
Boundary layer stability
Boundary layer transition
Classical Mechanics
Disturbances
Flat plates
Fluid- and Aerodynamics
Instability waves (fluids)
Mathematical Modeling and Industrial Mathematics
Mathematics
Mathematics and Statistics
Partial Differential Equations
Particle image velocimetry
Stability
Velocity measurement
Wind tunnels
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Summary:An artificial disturbance is introduced into the boundary layer over a flat plate to investigate the effect on the transition process in the Mach 6.5 wind tunnel at Peking University. A linear stability theory (LST) is utilized to predict the evolution of the eigenmodes, and the frequency of the artificial disturbance is chosen according to the LST results. The artificial disturbance is generated by glowing discharge on the surface of the plate close to the leading edge. The Rayleigh-scattering visualization and particle image velocimetry (PIV) measurements are performed. By comparing the experimental results with artificial disturbances with those under the natural condition (without artificial disturbances), the present paper shows that the second-mode instability waves are significantly stimulated by the artificial disturbances, and the boundary layer transition is effectively triggered.
ISSN:0253-4827
1573-2754
DOI:10.1007/s10483-019-2423-8