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Experimental investigation of blunt cone model at hypersonic Mach number 7.25

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A Correction to this article was published on 17 June 2021

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Abstract

Experiments were carried out in hypersonic shock tunnel in Defence Research and Directorate Laboratory at hypersonic Mach number of 7.25 using an 11.37° apex-angle blunt cone model. Heat flux measurement was carried out on cone model at different angles of attack with angle of rotation ϕ = 0° to 360° in steps of 45° with vacuum sputtered platinum thin film sensors. The measured experimental value of heat transfer data at stagnation point was compared with theoretical value estimated Fay and Riddell correlation. As angle of rotation was increased from ϕ = 0° to ϕ = 180°, the shock wave became closer to model surface due to high density ratio across the shock wave and consequently heat transfer rate became higher.

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Authors and Affiliations

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

    Saiprakash Mani

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

    C. Senthilkumar

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

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

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  1. Saiprakash Mani
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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 Saiprakash Mani.

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Technical Editor: André Cavalieri.

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The original online version of this article was revised due to a retrospective Open Access cancellation.

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Mani, S., Senthilkumar, C., Sunil, G.K. et al. Experimental investigation of blunt cone model at hypersonic Mach number 7.25. J Braz. Soc. Mech. Sci. Eng. 43, 216 (2021). https://doi.org/10.1007/s40430-021-02934-5

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  • DOI: https://doi.org/10.1007/s40430-021-02934-5

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