Abstract
Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.
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References
S.A. Gaponov and A.A. Maslov, Development of Disturbances in Compressible Flows, Nauka, Novosibirsk, 1980.
J. Laufer, Aerodynamic noise in supersonic wind tunnels. Aerospace Sci., 1961, Vol. 28, No. 9, P. 685–692.
J.M. Kendall, Wind-tunnel experiments relating to supersonic and hypersonic boundary-layer transition. AIAA J., 1975, Vol. 13, No. 3, P. 290–299.
V.G. Pridanov, A.M. Kharitonov, and V.V. Chernykh, Combined influence of the Mach and Reynolds numbers on transition in the boundary layer. Fluid Dynamics, 1974, Vol. 9, Iss. 1, P. 126–129.
R.A. King, Three-dimensional boundary-layer transition on a cone at Mach 3.5. Experiments in Fluids, 1992, Vol. 13, P. 305–314.
A.D. Kosinov, A.A. Maslov, and N.V. Semionov, An experimental study of generation of unstable disturbances on the leading edge of a plate at. J. Appl. Mech. Techn. Phys., 1997, Vol. 38, No. 1, P. 45–51.
N.V. Semionov and A.D. Kosinov, An experimental study of receptivity of supersonic boundary layer on a blunted plate. Int. J. Mechanics, 2008, Vol. 2, No. 3, P. 87–95.
S.P. Schneider, Effects of high-speed tunnel noise on laminar-turbulent transition. J. Spacecraft and Rockets, 2001, Vol. 38, No. 3, P. 323–333.
A.V. Vaganov, Yu.G. Ermolaev, A.D. Kosinov, N.V. Semionov, and V.I. Shalaev, Experimental study of flow structure and transition in the boundary layer of a delta wing with blunted leading edges at Mach numbers 2. 2.5, and 4, in: Proc. of the Moscow Physical-Technical Institute, 2013, Vol. 5, No. 3, P. 164–173.
A.V. Vaganov, Yu.G. Ermolaev, G.L. Kolosov, A.D. Kosinov, A.V. Panina, and N.V. Semionov, Action of incident Mach wave on the field of pulsations in boundary layer of a planar delta wing. Vestnik NGU, ser. Fizika, 2014, Vol. 9, No. 1, P. 29–38.
A.D. Kosinov, N.V. Semionov, Yu.G. Yermolaev, Disturbances in the test section of T-325 supersonic wind tunnel, Novosibirsk, 1999 (Preprint, ITAM SB RAS; No. 6–99).
A.V. Panina, A.D. Kosinov, Yu.G. Ermolaev. V.N. Gorev, and N.V. Semionov, Experimental study of mean and pulsation flow characteristics in the 2D/3D supersonic boundary layer behind flat roughness elements, Thermophysics and Aeromechanics, 2014, Vol. 21, No. 1, P. 3–13.
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This work was financially supported by the Russian Foundation for Basic Research (Grant No. 13-01-00520 a).
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Vaganov, A.V., Ermolaev, Y.G., Kolosov, G.L. et al. Impact of incident Mach wave on supersonic boundary layer. Thermophys. Aeromech. 23, 43–48 (2016). https://doi.org/10.1134/S0869864316010054
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DOI: https://doi.org/10.1134/S0869864316010054