Abstract
Shock relations usually found in literatures are derived theoretically under the assumption of homogeneous thermodynamic properties, i.e., constant ratio of specific heats, γ. However, high temperature effects post a strong shock wave may result in thermodynamic heterogeneities and failure to the original shock relations. In this paper, the shock relations are extended to take account of high-temperature effects. Comparison indicates that the present approach is more feasible than other analytical approaches to reflect the influence of γ heterogeneity on the post-shock parameters.
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Woods W C, Arlington J P, Hamilton H H. A review of preflight estimates of real-gas effects on space shuttle aerodynamic characteristics. In: Proceedings of Orbiter Experiments Aerothermodynamics Symposium. Hampton: NASA, 1983. 309–346
Maus J R, Griffith B J, Szema K Y, et al. Hypersonic Mach number and real gas effects on space shuttle orbiteraerodynamics. J Spacecraft Rockets, 1984, 21: 136–141
Brauckmann G J, Paulson J W, Weilmuenster K J. Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly. J Spacecraft Rockets, 1995, 32: 758–764
Bertin J J, Cummings R M. Critical hypersonic aerothermodynamic phenomena. Annu Rev Fluid Mech, 2006, 38: 129–157
Muylaert J, Walpot L, Rostand P, et al. Extrapolation from wind tunnel to flight: Shuttle orbiter aerodynamics. Technical Report. NASA, 1998
Holden M S, Wadhams T P, MacLean M, et al. Experimental studies in hypersonic flows for facility and code validation. AIAA Paper No. 2007-1304, 2007
Holden M S, Wadhams T P, MacLean M, et al. A review of basic research and development programs conducted in the LENS facilities in hypervelocity flows. AIAA Paper No. 2012-169, 2012
Park C. Hypersonic aerothermodynamics: Past, present and future. Int J Aeronaut Space Sci, 2013, 14: 1–10
Li K, Hu Z M, Jiang Z L. Numerical studies on the effect of the key parameter to hypersonic “pitch-up anomaly”. Sci Sin-Phys Mech Astron, 2015, 45: 034701
Furudate M, Nonaka S, Sawada K. Behavior of two-temperature model in intermediate hypersonic regime. J Thermophys Heat Transfer, 1999, 13: 424–430
Tirsky G A. Up-to-date gasdynamic models of hypersonic aerodynamics and heat transfer with real gas properties. Ann Rev Fluid Mech, 1993, 25: 151–181
Hirschel E H, Weiland C. Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles. Berlin: Springer-Verlag, 2009
Jiang Z L, Yu H R. Experiments and development of long test duration hypervelocity detonation-driven shock tunnel (LHDst). AIAA Paper No. 2014-1012, 2014
Anderson J D. Hypersonic and High Temperature Gas Dynamic. New York: McGraw-Hill, 1989
McBride B J, Zehe M J, Gordon S. NASA Glenn coefficients for calculating thermodynamic properties of individual species. Technical Report. NASA, 2002
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Hu, Z., Zhou, K., Peng, J. et al. Shock relations in gases of heterogeneous thermodynamic properties. Sci. China Technol. Sci. 60, 1050–1057 (2017). https://doi.org/10.1007/s11431-016-9007-6
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DOI: https://doi.org/10.1007/s11431-016-9007-6