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Effect of Aft Wall Offset on Supersonic Flow over Cavity

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Fluid Mechanics and Fluid Power – Contemporary Research

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

Abstract

A study is conducted on supersonic flow at Mach number 1.65 over rectangular cavity of length-to-depth (L/D) ratio 3. Schlieren visualization revealed normal shock train like pattern in flow over the cavity. These shock structure are unsteady, and oscillated longitudinally inside the test section over the cavity. The oscillating shock train is eliminated, as the blockage produced by shear layer and boundary layer thickening due to pressure recovery in cavity is reduced by offsetting the cavity aft wall. The shock train—shear layer coupling is observed to completely suppress the third and higher modes of cavity oscillations.

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Correspondence to Aravind Vaidyanathan .

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Maurya, P.K., Rajeev, C., Kumar, R.V., Aravind Vaidyanathan (2017). Effect of Aft Wall Offset on Supersonic Flow over Cavity. In: Saha, A., Das, D., Srivastava, R., Panigrahi, P., Muralidhar, K. (eds) Fluid Mechanics and Fluid Power – Contemporary Research. Lecture Notes in Mechanical Engineering. Springer, New Delhi. https://doi.org/10.1007/978-81-322-2743-4_5

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  • DOI: https://doi.org/10.1007/978-81-322-2743-4_5

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  • Publisher Name: Springer, New Delhi

  • Print ISBN: 978-81-322-2741-0

  • Online ISBN: 978-81-322-2743-4

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