Abstract
When a normal shock wave interacts with a boundary layer along a wall surface in supersonic internal flows and the shock is strong enough to separate the boundary layer, the shock is bifurcated and a series of shocks called “shock train” is formed. The flow is decelerated from supersonic to subsonic through the whole interaction region that is referred to as “pseudo-shock”. In the present paper some characteristics of the shock train and pseudo-shock and some examples of the pseudo-shocks in some flow devices are described.
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References
Om, D, Childs, M E. Multiple Transonic Shockwave/turbulent Boundary-layer Interaction in a Circular Duct. AIAA J., 1985, 23(5): 1506–1511
McCormick, D C. Shock/boundary-layer Interaction Control with Vortex Generators and Passive Cavity. AIAA J., 1993, 31(1): 91–96
Carroll, B F, Dutton, J C. Characteristics of Multiple Shock Wave/turbulent Boundary-layer Interactions in Rectangular Ducts. J. Propulsion and Power, 1990, 6(2): 186–193
Matsuo, K, Miyazato, Y, Kim, H D. Shock Train and Pseudo-shock Phenomena in Internal Gas Flows. Progress in Aerospace Sciences, 1999, 35(1): 33–100
Crocco, L. One-dimensional Treatment of Steady Gas dynamics. In Fundamentals of Gas Dynamics. Edited by H.W. Emmons. Princeton, U.S.A., 1958. 110–130
Waltrup, P J, Billig, F S. Structure of Shock Waves in Cylindrical Ducts. AIAA J., 1973, 11(10): 1404–1408
Waltrup, P J, Billig, F S. Prediction of Precombustion Wall Pressure Distributions in Scramjet Engines. J. of Spacecraft and Rockets, 1973, 10(9): 620–622
Sullins, G, McLafferty, G. Experimental Results of Shock Trains in Rectangular Ducts. AIAA Paper No.92-5103, 1992
Matsuo, K, Miyazato, Y, Kwon, J K, et al. Structure of Shock Trains in Constant Area Ducts. Experimental Heat Transfer, Fluid Mechnics and Thermodynmics, 2001, 3: 1859–1864
Neumann, E P, Lustwerk, F. Supersonic Diffusers for Wind Tunnels. J. Appl. Mech., 1949, 16(2): 195–202
Tamaki, T, Tomia, Y, Yamane, R. A Study of Pseudo-shock, 2nd Report, X-type Pseudo-shock. Bulletin of the JSME, 1971, 14(74): 807–817
Ostras, V N, Penzin, V I. Experimental Study of Friction in a Channel with a Pseudo-shock. Fluid Mechanics-Soviet Research, 1975, 4(6): 32–38
Merkli, P E. Pressure Recovery in Rectangular Constant Area Supersonic Diffusers. AIAA J., 1976, 14(2): 168–172
Ikui, T, Matsuo, K, Sasaguchi, K. Modified Diffusion Model of Pseudo-shock Waves Considering Upstream Boundary Layers. Bulletin of the JSME, 1981, 24(197): 1920–1927
Handbook of Supersonic Aerodynamics Sec. 17. Navweps Rep. 1488, 1964, .6 (Ed. I.D.V. Faro)
Ikui, T, Matsuo, K, Nagai, M. The Mechanism of Pseudo-shock Waves. Bulletin of JSME, 1974, 17(108): 731–739
Mahoney, J J. Inlets for Supersonic Missiles. American Institute of Aeronautics and Astronautics, Inc., 1990. 55–66
Curran, E T, Heiser, W H, Pratt, D T. Fluid Phenomena in Scramjet Combustion Systems. Annual Rev. Fluid Mech., 1996, 28: 323–360
Sajben, M, Donovan, J F, Morris, M J. Experimental Investigation of Terminal Shock Sensors for Mixed-compression Inlets. J. Propulsion & Power, 1992, 8(1): 168–174
Waltrup, P J, Billig, F S. Prediction of Precombustion Wall Pressure Distributions in Scramjet Engines. J. Spacecraft & Rockets, 1973, 10(9): 620–622
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Matsuo, K. Shock train and pseudo-shock phenomena in supersonic internal flows. J. of Therm. Sci. 12, 204–208 (2003). https://doi.org/10.1007/s11630-003-0068-y
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DOI: https://doi.org/10.1007/s11630-003-0068-y