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Hypersonic flow over a multi-step afterbody

Menezes, V and Kumar, S and Maruta, K and Reddy, KPJ and Takayama, K (2005) Hypersonic flow over a multi-step afterbody. In: Shock Waves, 14 (5&6). pp. 421-424.

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Effect of a multi-step base on the total drag of a missile shaped body was studied in a shock tunnel at a hypersonic Mach number of 5.75. Total drag over the body was measured using a single component accelerometer force balance. Experimental results indicated a reduction of 8% in total drag over the body with a multi-step base in comparison with the base-line (model with a flat base) configuration.The flow fields around the above bodies were simulated using a 2-D axisymmetric Navier-Stokes solver and the simulated results on total drag were compared with the measured results. The simulated flow field pictures give an insight into the involved flow physics.

Item Type: Journal Article
Publication: Shock Waves
Publisher: Springer
Additional Information: Copyright for this article belongs to Springer.
Keywords: Drag measurement;Stepped afterbody;Accelerometer balance;Hypersonic
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 14 Feb 2006
Last Modified: 19 Sep 2010 04:23
URI: http://eprints.iisc.ac.in/id/eprint/5350

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