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Aerothermodynamics of a hypersonic projectile with a double-disk aerospike

Published online by Cambridge University Press:  27 January 2016

R. Yadav  and
U. Guven
R. Yadav*
Affiliation:
University of Petroleum and Energy Studies, Dehradun, India
U. Guven*
Affiliation:
University of Petroleum and Energy Studies, Dehradun, India
*
[email protected]
[email protected]
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Abstract

The use of aerospikes at the nose of a hypersonic vehicle can substantially reduce its drag; however, the associated heat flux at the reattachment point is very high for turbulent flows. In this paper, the aerothermodynamics of a generic projectile model represented by a hemisphere- cylinder, fitted axisymmetrically with an aerospike at the nose is investigated numerically with a commercially available Navier Stokes Solver. The base model is a hemisphere-cylinder with a diameter of 40mm and an overall length of 70mm. An aerospike protrudes axisymmetrically at the nose of the base model and has a hemispherical cap from which another aerospike protrudes which again has a hemispherical cap, thus forming a double-disk aerospike. Compressible, axisymmetric Navier-Stokes Equations are solved for turbulent hypersonic flow of thermally perfect air with free stream conditions of Mach No 6·2 at standard sea level atmospheric conditions. The results for the model with double-disk aerospikes are compared with those of hemisphere-cylinder without aerospike. The results suggest that the use of double-disk aerospike can favourably reduce the turbulent reattachment heat flux along with suitable drag reduction of the main body.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1195 , September 2013 , pp. 913 - 928
Copyright
Copyright © Royal Aeronautical Society 2013 

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