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Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers

Menezes, Viren and Saravanan, S and Reddy, KPJ (2002) Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers. In: Shock Waves, 12 (3). pp. 197-204.

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A three-component accelerometer balance system is used to study the drag reduction effect of an aerodisc on large angle blunt cones flying at hypersonic Mach numbers. Measurements in a hypersonic shock tunnel at a freestream Mach number of 5.75 indicate more than 50% reduction in the drag coefficient for a 120degrees apex angle blunt cone with a forward facing aerospike having a flat faced aerodisc at moderate angles of attack. Enhancement of drag has been observed for higher angles of attack due to the impingement of the flow separation shock on the windward side of the cone. The flowfields around the large angle blunt cone with aerospike assembly flying at hypersonic Mach numbers are also simulated numerically using a commercial CFD code. The pressure and density levels on the model surface, which is under the aerodynamic shadow of the flat disc tipped spike, are found very low and a drag reduction of 64.34% has been deduced numerically.

Item Type: Journal Article
Publication: Shock Waves
Publisher: Springer
Additional Information: Copyright of this article belongs to Springer.
Keywords: drag reduction;spike;large angle blunt cone;hypersonic shock tunnel;accelerometer force balance
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 28 Jul 2011 07:05
Last Modified: 28 Jul 2011 07:05
URI: http://eprints.iisc.ac.in/id/eprint/39398

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