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CFD Simulation of Hypersonic Shock Tunnel Nozzle

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Recent Advances in Theoretical, Applied, Computational and Experimental Mechanics

Part of the book series: Lecture Notes in Mechanical Engineering ((LNME))

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Abstract

The design of a hypersonic nozzle for shock tunnel is of much importance as it plays a vital role in generating the required flow field. The computational simulation can help to understand the Mach number distribution inside the test section. This can help to design the mounting assembly for the model and to limit the dimension of the model. The flow field for an axisymmetric test section has been analysed using commercial software. The results revealed the variation of Mach number inside the test section and exit plane of the nozzle.

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References

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Author information

Authors and Affiliations

  1. Department of Aerospace Engineering, Amity School of Engineering & Technology, Amity University Mumbai, Panvel, Maharashtra, India

    Jigarkumar Sura

Authors
  1. Jigarkumar Sura
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Correspondence to Jigarkumar Sura .

Editor information

Editors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, India

    B. N. Singh

  2. Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, India

    Arnab Roy

  3. Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, India

    Dipak Kumar Maiti

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Sura, J. (2020). CFD Simulation of Hypersonic Shock Tunnel Nozzle. In: Singh, B., Roy, A., Maiti, D. (eds) Recent Advances in Theoretical, Applied, Computational and Experimental Mechanics. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-1189-9_30

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  • DOI: https://doi.org/10.1007/978-981-15-1189-9_30

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-15-1188-2

  • Online ISBN: 978-981-15-1189-9

  • eBook Packages: EngineeringEngineering (R0)

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