[1] Peng, Y., Gerdroodbary, M.B., Sheikholeslami, M., Shafee, A., Babazadeh, H., Moradi, R., Mixing enhancement of the multi hydrogen fuel jets by the backward step, Energy, 203, 2020, 25438-25451.
[2] Liu, X., Gerdroodbary, M.B., Sheikholeslami, M., Moradi, R., Shafee, A., Li, Z., Effect of strut angle on performance of hydrogen multi-jets inside the cavity at combustion chamber, International Journal of Hydrogen Energy, 45(55), 2020, 31179-31187.
[3] Nagai, H., Yang, H.S., Ueta, Y., Murakami, M., Takano, N., Yanaka, K., Application of super fluid shock tube facility to experiments of highly transient low-temperature thermo-fluid dynamic phenomena, Cryogenics, 41(5-6), 2001, 421-428.
[4] Buttsworth, D., Jones, T., High bandwidth stagnation temperature measurements in a Mach 6 gun tunnel flow, Experimental Thermal and Fluid Science, 27(2), 2003, 177-186.
[5] Moradi, A., Khodadadiyan, S., Study of real gas behavior in a single-stage gas gun, International Journal of Mechanical and Mechatronics Engineering, 78, 2011, 83-87.
[6] Hamamoto, N., Kawazoe, H., Nakamura, Y., Arai, N., Kitagawa, K., Spectroscopic study of high enthalpy flow around a blunt body in arc-heated wind tunnel, Energy Conversion and Management, 38(10-13), 1997, 1177-1186.
[7] Stalker, R., Plumb, D., Diaphragm-type Shock Tube for High Shock Speeds, Nature, 218, 1968, 789-790.
[8] Smy, P., Electromagnetic Shock Tube capable of producing a Well-formed shock Wave of Low Attenuation, Nature, 193, 1962, 969-970.
[9] Drummond, L., Exothermic Reactions behind a Reflected Shock, Nature, 216, 1967, 787-789.
[10] Itoh, K., Ueda, S., Tanno, H., Komuro, T., Sato, K., Hypersonic aerothermodynamic and scramjet research using high enthalpy shock tunnel, Shock Waves, 12, 2002, 93-98.
[11] Al-Falahi, A., Yusoff, M.Z., Ahmed, D.I., Shuaib, N.H., Experimental performance evaluation of short duration high speed flow shock tunnel, 3rd International Conference on Energy and Environment (ICEE), Malacca, Malaysia, 2009.
[12] Stollery, J. Stagnation Temperature Measurements in a Hypersonic Wind-Tunnel using the Sodium Line Reversal Method, Nature, 190, 1961, 778–779.
[13] Trivedi, S., Menezes, V., Measurement of yaw, pitch and side-force on a lifting model in a hypersonic shock tunnel, Measurement, 45(7), 2012, 1755-1764.
[14] Yu, M.S., Heat Transfer by Shock-wave/boundary Layer Interaction on a Flat Surface with a Mounted Cylinder, International Journal of Heat and Mass Transfer, 55, 2012, 1764-1772.
[15] Pennelegion, L., A Microwave Method of determining the Displacement and Velocity of a Piston in a Hypersonic Gun Tunnel, Nature, 183, 1959, 246.
[16] Askari, S., An analytical approach for stand-off distance of detached shock waves, Aerospace Science and Technology, 28(1), 2013, 384-390.
[17] Diyar, I.A., Al-Falahi, A., Yusoff, M.Z., Shuaib, N.H., Two dimensional numerical investigations on the velocity profile in a shock tunnel, European Journal of Scientific Research, 45(3), 2010, 458-469.
[18] Vadassery, P., Joshi, D.D., Rolim, T.C., Lu, F.K., Design and Testing of an External Drag Balance for a Hypersonic Shock Tunnel, Measurement, 46(7), 2013, 2110-2117.
[19] Banerjee, A., Analysis of shock waves over novel supersonic aircraft profiles using shadowgraph, IEEE Aerospace Conference, Big Sky, MT, USA, 2010.
[20] Belcher, B., Measurement of the Effects of Piston Mass and Bursting Pressure on the Motion of a Piston in a Hypersonic Gun Tunnel, Nature, 184, 1959, 1207-1209.
[21] Mallinson, S., Hillier, R., Jackson, A., Ki, D., Gun tunnel flow calibration: defining input conditions for hypersonic flow computations, Shock Waves, 10, 2000, 313-322.
[22] Edney, E., Temperature Measurements in a Hypersonic Gun Tunnel Using Heat Transfer Methods, Journal of Fluid Mechanics, 27(3), 1967, 503-512.
[23] Mohsen, A.M., Yusoff, M.Z., Hasini, H., Al-Falahi, A., Two-dimensional computational modeling of high-speed transient flow in gun tunnel, Shock Waves, 28(2), 2018, 335-348.
[24] Sheng, Y., Liu, J., A computational technique for high enthalpy shock tube and shock tunnel flow simulation, Shock Waves, 8, 1998, 203-214.
[25] Jacobs, P., Quasi-one-dimensional modeling of a free-piston shock tunnel, AIAA Journal, 32(1), 1994, 137-145.
[26] Misawa, T., Ogawa, H., Fujiwara, T., Numerical analysis of viscous, Nonequilibrium, hypervelocity flow induced by a free piston shock tunnel, 21st International Symposium on Shock Waves, Great Keppel Island, Australia,1997.
[27] Peng, Y., Gerdroodbary, M.B., Sheikholeslami, M., Shafee, A., Babazadeh, H., Moradi, R., Mixing enhancement of the multi hydrogen fuel jets by the backward step, Energy, 203, 2020, 1-9.
[28] Al-Falahi, A., Yusoff, M.Z., Yusaf, T., Numerical simulation of inviscid transient flows in shock tube and its validations, International Journal of Mechanical, Aerospace, Industrial and Mechatronics Engineering, 2(7), 2008, 1-11.
[29] Al-Falahi, A., Yusoff, M.Z., Yusaf, T., Numerical and Experimental Study to Evaluate the Performance of Universiti Tenaga Nasional Short Duration Hypersonic Test Facility, 16th Australasian Fluid Mechanics Conference, School of Engineering, The University of Queensland, Australia,2007.
[30] Mohsen, A.M., Yusoff, M.Z., Al-Falahi, A., Shuaib, N.H., The Effects of Area Contraction on Shock Wave Strength and Peak Pressure in Shock Tube, International Journal of Automotive and Mechanical Engineering, 5, 2012, 587-596.
[31] Mohsen, A.M., Yusoff, M.Z., Al-Falahi, A., Area Contraction Effect on Shock Tube Performance, Numerical and Experimental Study, Journal of Engineering and Applied Sciences, 10(20), 2015, 9614-9620.
[32] Andreotti, R., Colombo, M., Guardone, A., Martinelli, P., Riganti, G., Prisco, M., Performance of a shock tube facility for impact response of structures, International Journal of Non-Linear Mechanics, 72, 2015, 53-66.
[33] Kotov, Yee, H., Panesi, M., Prabhu, D., Wray, A., Computational challenges for simulations related to the NASA electric arc shock tube (EAST) experiments, Journal of Computational Physics, 269, 2014, 215-233.
[34] Mundt, Boyce, R., Jacobs, P., Hannemann, K., Validation study of numerical simulations by comparison to measurements in piston-driven shock-tunnels, Aerospace Science and Technology, 11(2), 2007, 100-109.
[35] Liou, M.S., Wada, Y., An accurate and robust flux splitting scheme for shock and contact discontinuities, SIAM Journal on Scientific Computing, 18, 1997, 633-657.
[36] Warming, R.F., Beam, R.M., Upwind second order difference schemes and applications in aerodynamic flows, AIAA Journal, 14(9), 1976, 1242-1249.
[37] VanLeer, B., Towards the ultimate conservative difference scheme vs a second order sequel to godunov's sequel, Journal of Computational Physics, 32, 1979, 101-136.
[38] Lamnaouer, M., Numerical modeling of the shock tube flow fields before and during ignition delay time experiments at practical conditions, Ph.D. Thesis, University of Central Florida Orlando, 2010.
[39] Kryukov, I.A., Ivanov, I.E., Shock wave - boundary layer interaction in a long shock tube, IOP Conf. Series: Journal of Physics: Conf. Series, Moscow, Russian Federation, 1009- 012010, 2010.
[40] Musgrove, P.J., Appleton, J.P., The influence of boundary layer growth on shock tube test times, Applied Scientific Research, 18, 1968, 116–155.
[41] Hideyuki, T., Tomoyuki, K., Kazuo, S., Katsuhiro, I., Free-flight force measurement technique in the impulsive facility HIEST, 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, Pacific Grove, CA, USA, 2007.
[42] Robinson, M.J., Meet, D.J., Three-Component Force Measurements on a Large Scramjet in a Shock Tunnel, Journal of Spacecraft and Rockets, 41(3), 2004, 416-425.
[43] Wang, Y., Hu, Z., Liu, H., Jiang, Z., Starting Process in a Large-Scale Shock Tunnel, AIAA Journal, 54(4), 2016, 1240-1249.
[44] Robinson, M.J., Schramm, J.M., Hannemann. K., An internal stress wave force balance for use in a shock tunnel, Record International Congress on Instrumentation in Aerospace Simulation Facilities, 2005, 100-109.