Abstract
The effect of a Mach wave (N wave) on laminar-turbulent transition induced by the first instability mode (Tollmien–Schlichting wave) in the flat-plate boundary layer is investigated on the basis of the numerical solution of Navier–Stokes equations at the freestream Mach number of 2.5. In accordance with the experiment, the N wave is generated by a two-dimensional roughness at the computation domain boundary corresponding to the side wall of the test section of a wind tunnel. It is shown that the disturbance induced by the backward front of the N wave in the boundary layer has no effect on the beginning of transition but displaces downstream the nonlinear stage of the first mode development. The disturbance induced by the forward front of the N wave displaces the beginning of transition upstream.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
S. R. Pate, “On Boundary-Layer Transition in Supersonic-HypersonicWind Tunnels. Theory and Application,” AEDC-TR-77-107, Arnold Engineering Development Center, Tennessee (1978).
A. V. Vaganov, Yu. G. Ermolaev, G. L. Kolosov, A. D. Kosinov, A. V. Panina, and N. V. Semenov, “Effect of an Incident MachWave on the Fluctuation Field in the Boundary Layer in Flow over a Planar DeltaWing,” Vestn. Novosibirsk Gos. Un-ta, Ser. Fizika 9 (1), 29 (2014).
A. V. Vaganov, Yu. G. Ermolaev, A. D. Kosinov, A. V. Panina, and V. I. Shalaev, “Experimental Investigation of the Flow Structure and Transition in the Boundary Layer on a DeltaWing with Blunted Leading Edges at Mach Numbers 2, 2.5, and 4,” Tr.MFTI 5 (3), 164 (2013).
A. V. Vaganov, Yu. G. Ermolaev, G. L. Kolosov, A. D. Kosinov, A. V. Panina, N. V. Semionov, and A. A. Yatskikh, “Impact of Incident Mach Wave on Supersonic Boundary Layer,” Thermophysics Aeromechanics 23 (1), 43 (2016).
Q. H. Din, I. V. Egorov, and A. V. Fedorov, “Interaction between Mach Waves and the Boundary Layer in Supersonic Flow past a Plate with a Sharp Leading Edge,” Uch. Zap. TsAGI 48 (4), 10 (2017).
L. M. Mack, “Boundary-Layer Stability Theory,” Jet Propulsion Lab., Pasadena, Ca, Internal Document 900–277 (1969).
I. V. Egorov and A. V. Novikov, “Direct Numerical Simulation of Laminar-Turbulent Flow past a Flat Plate at Hypersonic Velocities,” Zh. Vychisl.Mat.Mat. Fiz. 56 (6), 1064 (2016).
G.-S. Jiang and C.-W. Shu, “Efficient Implementation ofWeighted ENO Schemes,” J. Comput. Phys. 126 (1), 202 (1996).
A. Novikov and I. Egorov, “Direct Numerical Simulations of Transitional Boundary Layer over a Flat Plate in Hypersonic Free-Stream,” AIAA Paper No. 3952 (2016).
A. Novikov, I. Egorov, and A. Fedorov, “Direct Numerical Simulation of Wave Packets in Hypersonic Compression-Corner Flow,” AIAA J. 54 (7), 2034 (2016).
C. S. J. Mayer, D. A. von Terzi, and H. F. Fazel, “DNS of Complete Transition to Turbulence via Oblique Breakdown atMach 3,” AIAA Paper No. 4398 (2008).
H. Schlichting and K. Gersten, Boundary Layer Theory (Springer, New York, 2000).
Author information
Authors and Affiliations
Corresponding author
Additional information
Original Russian Text © Q.H. Din, I.V. Egorov, A.V. Fedorov, 2018, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2018, No. 5, pp. 113–124.
Rights and permissions
About this article
Cite this article
Din, Q.H., Egorov, I.V. & Fedorov, A.V. Mach Wave Effect on Laminar-Turbulent Transition in Supersonic Flow over a Flat Plate. Fluid Dyn 53, 690–701 (2018). https://doi.org/10.1134/S0015462818050063
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1134/S0015462818050063