بررسی عددی تأثیر نسبت فشاری بر پدیده تداخل موج ضربه‌ای و لایه‌مرزی در یک مجرا با سطح مقطع ثابت

[[1]] Green J.E., Interactions Between Shock Waves and Turbulent Boundary Layers, Progress Aerospace Sciences, Vol. 11, pp. 235-340, 1970.

[2] Weiss A., Grzona A., Olivier H., Behavior of shock trains in a diverging duct, Experiments in Fluids, Vol. 49, No. 2, pp. 355–365,2010.

[3] Huang W., Wang Z., Pourkashanian M., Ma L., Ingham D.B., Luo S.b., Lei J., Liu J., Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator, Elsevier, Vol. 68, Issues 11-12, pp. 1669-1675, June-July 2011.

[4] Neumann E.P., Lustwerk F., Supersonic Diffusers for Wind Tunnels, Journal of Applied Mechanics, Vol. 16, No. 2, pp.195-202,1949.

[5] Akatsuka J., Nagai S., The Effect of Diffuser Geometry on the Starting Pressure Ratio of a Supersonic Wind Tunnel, 27th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, Chicago, Illinois, 28 June - 1 July 2010.

[6] Lukasiewicz J., Diffusers for Supersonic Wind Tunnels, Journal of the Aeronautical Sciences, Vol. 20, No. 9, pp. 617-626, 1953.

[7] Shapiro A.H., The Dynamics and Thermodynamics of Compressible Fluid Flow, New York: Ronald Press, Vols. 1 & 2, pp. 135-139& 1153-1156, 1953.

[8] Soltani M.R., Abedi M., SepahiYounsi J., Experimental Investigation of Instability of a Supersonic Mixed Compression Air Intake, Modares Mechanical Engineering, Vol. 15, No.4, pp. 93-100, 2015

[9] Ikui T., Matsuo K., Researches of Supersonic Flow with the Shock Wave as Main Subject, JSME Journal (in Japanese),Vol. 72, No. 609, pp.1306-1312,1969.

[10] Kim H., Shock Induced Boundary Layer Separation, 8th International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows, Lyon, France, 2007.

[11] Om D., Childs M.E., Multiple Transonic Shock-Wave/Turbulent Boundary-Layer Interaction in a Circular Duct, AIAA Journal, Vol. 23, No. 10, pp.1506-1511, 1985.

[12] Tamaki T., Tomita Y., Yamane R., A study of Sseudo-Shock, 1st Report, λ-type pseudo-shock, Bull JSME, Vol. 13, No.55, pp.51-58, 1970.

[13] Tamaki T., Tomita Y., Yamane R., A study of pseudo-shock, 2nd Report, X-type pseudo-shock, Bull JSME, Vol. 14, No. 74, pp. 807-817, 1971.

[14] Ikui T., Matsuo K., Nagai M., The mechanism of pseudo-shock waves, Bull JSME, Vol. 17, No. 108, pp.731-739, 1974.

[15] McCormick DC., Shock/boundary-layer interaction control with vortex generators and passive cavity, AIAA Journal, Vol. 31, No. 1, pp.91-96, 1993.

[16] Carroll BF., Dutton JC., Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts, Journal of Propulsion Power, Vol. 6, No. 2, pp.186-193, 1990.

[17] Shope F.L., Contour design techniques for super /hypersonic wind tunnel nozzles, AIAA, 24thApplied Aerodynamics Conference, San Francisco, California, June 5-8, 2006.

[18] Al-Ajlouni M., An automatic method for creating the profile of supersonic convergent-divergent nozzle, Journal of Mechanical and Industrial Engineering, Vol. 4, No. 3, pp. 404-411, June 2010.

[19] Sugiyama H., Fukuda K., Mizobata K., Sun L., Minato R., Experimental Investigation on Shock Wave and Turbulent Boundary Layer Interactions in a Square Duct at Mach 2 and 4, Proceedings of the international gas turbine congress, Tokyo, Japan, November 2-7, 2003.

[20] Carroll B. F., Dutton J. C., Turbulence Phenomena in a Multiple Normal Shock Wave/Turbulent Boundary-Layer Interaction, AIAA Journal, Vol. 30, No. 1, pp. 43-48, January 1992.

[21] Helmer D. B., Measurements of a Three-Dimensional Shock-Boundary Layer Interaction, PhD Thesis, Department of Mechanical Engineering, Stanford University, Stanford, July 2011.

[22] Miyazato Y., Matsuo K., Kasada R., Experimental and Theoretical Investigations of Normal Shock Wave/Turbulent Boundary-Layer Interactions at Low Mach Numbers in a Square Straight Duct, 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition, Orlando, Florida, January 5 – 8, 2009.

[23] Sun L., Sugiyama H., Mizobata K., Fukuda K., Numerical and Experimental Investigations on the Mach 2 Pseudo-Shock Wave in a Square Duct, Journal of Visualization, Vol. 6, No. 4,pp. 363-370 , 2003.

]24[ Wong W.S., Qina N., Sellars N., Holden H., Babinsky H., A combined experimental and numerical study of flow structures over three-dimensional shock control bumps, Aerospace Sciences and Technology, Vol. 12, Issue 6, pp. 436–447,September 2008.

[25] Wilcox D.C., Turbulence modeling for CFD, First Edition, pp. 84-87, DCW Industries, 2006.

[26] Ockfen A.E., Viscous modeling of ground effect aerodynamics of Airfoil and jet, M.S. Thesis, Department of Mechanical Engineering, Washington State University, Washington DC, USA, 2008.

[27] Holden H. A., Babinsky H., Separated Shock–Boundary-Layer Interaction Control Using Streamwise Slots, Journal of Aircraft, Vol. 42, No. 1, Feb. 2005.

[28] Matsuo K., Miyazato Y., Kim H.D., Shock train and pseudo-shock phenomena in internal gas flows, Progress in Aerospace Sciences, Vol. 35, Issue 1, pp. 33-100,1999.