ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Hypersonic flow past a spherically blunted nose cone: A computational study

Narayan, A and Narayanan, S and Kumar, R and Kumar, CS and Jagadeesh, G (2020) Hypersonic flow past a spherically blunted nose cone: A computational study. In: Hypersonic flow past a spherically blunted nose cone: A computational study, pp. 105-123.

Full text not available from this repository.
Official URL: https://dx.doi.org/10.1504/PCFD.2020.106410


The present study investigates the aerodynamic characteristics of spherically blunted nose cone at a hypersonic Mach number of 5.8, numerically. The studies are conducted for different combinations of bluntness ratios and semi-cone angles, at zero angle of attack, in order to ascertain the nose cone parameters which provide minimum aerodynamic drag coefficient. The velocity vector shows the flow deceleration near the nose, re-acceleration through the sides as well the formation of recirculation zones. The structure of bow shock formed ahead of the nose as well as shock detachment distance is depicted by the Mach number contours. It is observed that the shock detachment distance follows linearly increasing behaviour with increase in bluntness ratios for all semi-cone angles studied. An empirical expression is developed for the shock detachment distance using the regression analysis, which reveals that it is mainly a function of bluntness ratio. It is observed that the aerodynamics drag coefficient attains a minimum value for smaller, bluntness ratios and semi-angle. Further, the aerodynamic drag coefficient is observed to be a strong function of bluntness ratios for smaller semi-cone angles. Copyright © 2020 Inderscience Enterprises Ltd.

Item Type: Conference Paper
Publication: Progress in Computational Fluid Dynamics
Publisher: Inderscience Enterprises Ltd.
Additional Information: The copyright for this article belongs to Inderscience Publishers
Keywords: Angle of attack; Drag coefficient; Hypersonic flow; Mach number; Nose cones; Regression analysis, Aerodynamic characteristics; Bluntness ratios; Computational studies; Empirical expression; Re-acceleration; Recirculation zones; Shock detachment; Velocity vectors, Aerodynamic drag
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 03 Nov 2021 09:30
Last Modified: 03 Nov 2021 09:30
URI: http://eprints.iisc.ac.in/id/eprint/65235

Actions (login required)

View Item View Item