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Effect of nose shape on the shock standoff distance at nearsonic flows

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Thermophysics and Aeromechanics Aims and scope

Abstract

This paper describes a numerical solution of the bow shock shape ahead of some blunt and sharp axisymmetric noses containing sphere, blunt cone, and sharp cone at steady transonic flow in the Mach number range of 1.01 to 1.2. For validating the results, one sphere and three blunt cones are modeled, and their shock standoff distance is compared with other experimental and numerical studies. The flow over other noses with similar geometric parameters is then solved and compared with each other. In this study, the Reynolds-averaged Navier—Stokes equations are solved using the Spalart—Allmaras turbulence model. The purpose of this study is to determine the shock standoff distance for some blunt and sharp noses at low supersonic free flight speed. The shock standoff distance is determined from the Mach number curve on the symmetry line. The present numerical simulations reach down to M8=1.01 a range where it is almost very difficult to set in experimental studies. The shock wave locations were found to agree well with previous numerical and experimental studies. Our results are closer to the experimental results compared to other numerical studies. In addition, the results for shock standoff distances over paraboloids in these speed ranges have not been previously published as far as we know.

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  1. Amirkabir University of Technology, Tehran, Iran

    Z. Eghlima & K. Mansour

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  1. Z. Eghlima
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  2. K. Mansour
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Correspondence to K. Mansour.

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Eghlima, Z., Mansour, K. Effect of nose shape on the shock standoff distance at nearsonic flows. Thermophys. Aeromech. 23, 499–512 (2016). https://doi.org/10.1134/S086986431604003X

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  • DOI: https://doi.org/10.1134/S086986431604003X

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