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Shock wave standoff distance of near space hypersonic vehicles

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Abstract

The shock wave standoff distances of near space hypersonic vehicles, which execute missions mainly at the altitude of 25 km to 55 km, are vital in aerothermodynamic analysis. The implicit finite volume schemes are derived from axisymmetric Navier-Stokes equations for chemical equilibrium flow, and programmed in FORTRAN. Taking a sphere cone for example, the effects of Mach numbers (from 22 to 36) on the shock wave standoff distance and the average density behind the shock are simulated at different altitudes from 25 km to 55 km. The numerical results illustrate that the turning point of the standoff distance is corresponding to that of the average density with the variation of Mach numbers. Based on the numerical results, we propose a formula for shock wave standoff distance, which is the function of the radius of the blunt body, the Mach number and the altitude in the atmosphere. Compared with previous correlations, the new formula can overcome the drawbacks of larger relative errors and complex calculations of the average density.

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Authors and Affiliations

  1. Institute of Engineering Mechanics, Beijing Jiaotong University, Beijing, 100044, China

    YuMeng Hu, HaiMing Huang & Jin Guo

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  1. YuMeng Hu
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  2. HaiMing Huang
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  3. Jin Guo
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Correspondence to HaiMing Huang.

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Hu, Y., Huang, H. & Guo, J. Shock wave standoff distance of near space hypersonic vehicles. Sci. China Technol. Sci. 60, 1123–1131 (2017). https://doi.org/10.1007/s11431-016-9055-5

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  • DOI: https://doi.org/10.1007/s11431-016-9055-5

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