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Investigation of Slender Bodies at Hypersonic Mach Numbers

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Abstract—

Tests were carried in a shock tunnel to determine the heating rate and the wall pressure on a test model flying at hypersonic velocity. The experiments were performed at Mach M = 6.5 and a total enthalpy of 1.2 MJ/kg. Helium was used as the driver gas and air as the driven gas. The effective test time during the tunnel testing was 3.5 ms. The vacuum sputtered gages were used to evaluate the heating rate on the test model. The evaluated heating rate agrees well with numerical simulation. The experimentally measured pressure also agrees with computational fluid dynamics

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Authors and Affiliations

  1. Department of Aerospace Engineering, MLR Institute of Technology, Telangana, India

    M. Saiprakash

  2. Department of Aerospace Engineering, MIT Campus, Anna University, 600044, Chennai, India

    C. Senthilkumar

  3. Directorate of Aerodynamics, Defence Research & Development Laboratory, 500058, Hyderabad, India

    G. Kadam sunil, Singh Prakash Rampratap, V. Shanmugam & G. Balu

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  1. M. Saiprakash
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  2. C. Senthilkumar
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  3. G. Kadam sunil
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  4. Singh Prakash Rampratap
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  5. V. Shanmugam
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  6. G. Balu
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Correspondence to M. Saiprakash, C. Senthilkumar, G. Kadam sunil, Singh Prakash Rampratap, V. Shanmugam or G. Balu.

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Saiprakash, M., Senthilkumar, C., Kadam sunil, G. et al. Investigation of Slender Bodies at Hypersonic Mach Numbers. Fluid Dyn 56, 255–261 (2021). https://doi.org/10.1134/S0015462821020087

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  • DOI: https://doi.org/10.1134/S0015462821020087

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