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Forward facing spike effects on bodies of different cross section in supersonic flow

Published online by Cambridge University Press:  04 July 2016

G. R. Hutt  and
A. J. Howe
G. R. Hutt
Affiliation:
Department of Aeronautics and Astronautics, The University of Southampton
A. J. Howe
Affiliation:
Department of Aeronautics and Astronautics, The University of Southampton
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Extract

The results of an experimental programme conducted in the University of Southampton's induced flow supersonic wind tunnel are presented. The pitch static force coefficient and centre of pressure data relate to a series of bodies with a blunt cone nose forebody with afterbodies comprising circular, square and triangular cross section. The blunt cone nose forebody has a forward located, body axis, aerodynamic spike system.

The data presented reveals the well known benefits of aerospikes with blunt nosed axisymmetric vehicles. This is then used as a base to explore the coupled flowfield effects on force coefficients due to spike deployment on bodies of non-axisymmetric cross section. The results identify how the body-only benefits of triangular cross sections are not degraded by the spike presence, with the main aero-spike benefit of drag reduction preserved throughout the angle of attack range investigated.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 926 , July 1989 , pp. 229 - 234
Copyright
Copyright © Royal Aeronautical Society 1989 

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References

1. Beastall, D. and Turner, J. The Effect of a Spike Protruding in Front of a Bluff Body at Supersonic Speeds. ARC R & M No. 3007, 1957.Google Scholar
2. Hunt, G. K. Supersonic Wind Tunnel Study of Reducing the Drag of a Bluff Body at Incident by Means of a Spike. RAE Report Aero 2606, 1958.Google Scholar
3. Zorea, C. and Rom, J. Effect of a spike on the drag and on the aerodynamic stability of blunt bodies in supersonic flow. J Spacecraft Rockets, Aug. 1970, 7, pp 1017–1019.Google Scholar
4. Bogdonoff, S. M. and Vas, I. E. Preliminary investigations of spiked bodies at hypersonic speeds, J Aero/Space Sci, 1959, 26, (2), pp 65–74.Google Scholar
5. Maull, D. J. Hypersonic flow over axially symmetric spiked bodies, J Fluid Mech, 1960, 8, Pt. IV, pp 584–592.Google Scholar
6. Wood, C. J. Hypersonic flow over spiked cones, J Fluid Mech, 1961, 122, Pt. IV, pp 614–624.Google Scholar
7. Hutt, G. R. and East, R. A. Static and dynamic pitch stability of a blunted cone with forward facing aerodynamic spike in hypersonic flow, Aeronaut J, Oct. 1985, 89, (888), pp 307–314.Google Scholar
8. Jackson, C. M. and Sawyer, W. C. Bodies with non-circular cross sections and bank-to turn missiles. Tactical Missile Aerodynamics. Progress in Astronautics and Aeronautics, AIAA 1986.Google Scholar
9. Daniel, D. C., Lijweski, L. E. and Zollars, G. F. Experimental Aerodynamic Studies of Missile With Square Cross Sections. Proceedings of NATO AGARD-CP-336. Missile Aerodynamics Symposium 1982.Google Scholar
10. Schneider, W. Experimental Investigation of Bodies With Non-Circular Cross Section in Compressible Flow. Proceedings of NATO AGARD-CP-336. Missile Aerodynamics Symposium 1982.Google Scholar
11. Hutt, G. R. and Howe, A. J. Effects of cross section and nose geometry on slender body supersonic aerodynamics, J Spacecraft Rockets, 1988, 25, 2.Google Scholar
12. Reding, J. P., Guenther, R. A. and Richter, B. J. Unsteady aerodynamic considerations in the design of a drag reduction spike, J Spacecraft Rockets, 1977, 14, pp 54–60.Google Scholar