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Experimental investigation on spiked body in hypersonic flow

Published online by Cambridge University Press:  03 February 2016

R. Kalimuthu ,
R. C. Mehta  and
E. Rathakrishnan
R. Kalimuthu
Affiliation:
Vikram Sarabhai Space Center, Trivandrum, India
R. C. Mehta
Affiliation:
Nanyang Technological University, Singapore
E. Rathakrishnan
Affiliation:
Indian Institute of Technology, Kanpur, India
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Abstract

A spike attached to a hemispherical body drastically changes its flowfield and influences aerodynamic drag in a hypersonic flow. It is, therefore, a potential candidate for drag reduction of a future high-speed vehicle. The effect of the spike length, shape, spike nose configuration and angle-of-attack on the reduction of the drag is experimentally studied with use of hypersonic wind-tunnel at Mach 6. The effects of geometrical parameters of the spike and angle-of-attack on the aerodynamic coefficient are analysed using schlieren picture and measuring aerodynamic forces. These experiments show that the aerodisk is superior to the aerospike. The aerodisk of appropriate length, diameter and nose configuration may have the capability for the drag reduction. The inclusion of an aero disk at the leading edge of the spike has an advantage for the drag reduction mechanism if it is at an angle-of-attack, however consideration to be given for increased moment resulting from the spike is required.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1136 , October 2008 , pp. 593 - 598
Copyright
Copyright © Royal Aeronautical Society 2008 

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