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The Effect of Sting Diameter and Length on Base Pressure at M = 3·88

Published online by Cambridge University Press:  07 June 2016

Walter R. Sieling
Walter R. Sieling*
Affiliation:
Rutgers—The State University, New Jersey, USA
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Summary

The effects of sting diameter and cylindrical protuberance length on the base pressure of an axisymmetric body in a turbulent supersonic flow are experimentally determined. It is found that the change in base pressure due to the presence of the sting is greater than 4 per cent when the ratio of sting diameter to base diameter is 0·150 or greater. When the ratio of cylindrical protuberance length to base diameter is greater than 1·3 there is no apparent change in base pressure with a change in length. However, when this ratio is less than 1·3, the base pressure varies greatly with length.

Type
Research Article
Information
Aeronautical Quarterly , Volume 19 , Issue 4 , November 1968 , pp. 368 - 374
Copyright
Copyright © Royal Aeronautical Society. 1968

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References

1. Przirembel, C. E. G. Construction and operation of RANT. Rutgers—The State University, Department of Mechanical and Aerospace Engineering, 110-ME-F, November 1966.Google Scholar
2. Reid, J. and Hastings, R. C. Experiments on the axisymmetric flow over afterbodies and bases at M =2·0. Royal Aircraft Establishment, Report Aero. 2628, October 1959.Google Scholar
3. Donaldson, T. S. The effect of sting supports on the base pressure of a blunt-based body in a supersonic stream. The Aeronautical Quarterly, Vol. VI, p. 221, August 1955.CrossRefGoogle Scholar
4. Chapman, D. R. An analysis of base pressure at supersonic velocities and comparison with experiment. NACA TN 2137, July 1950.Google Scholar
5. Perkins, E. W. Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1·5. NACA TN 2292, 1951.Google Scholar
6. Reller, J. O. and Hamaker, F. M. An experimental investigation of the base pressure characteristics of non-lifting bodies of revolution at Mach numbers from 2·73 to 4·98. NACATN 3393, March 1955.Google Scholar
7. Srvier, K. R. and Bogdonoff, S. M. The effect of support interference on the base pressure of a body of revolution at high Reynolds numbers. Princeton University Report 322, October 1955.Google Scholar
8. Kavanau, L. L. Base pressure studies in rarefied supersonic flows. Journal of the Aeronautical Sciences, Vol. 23, p. 193, March 1956.Google Scholar
9. Bogdonoff, S. M. A preliminary study of Reynolds number effects on base pressure at M = 2·95. Journal of the Aeronautical Sciences, Vol. 19, p. 201, March 1952.CrossRefGoogle Scholar
10. Whitfield, J. D. Critical discussion of experiments on support interference at supersonic speeds. Arnold Engineering Development Center, AEDC TN-58-30, August 1958.Google Scholar
11. Zarin, N. A. Base pressure measurements on sharp and blunt 9° cones at Mach numbers from 3·50 to 9·20. AlAA Journal, Vol. 4, p. 743, April 1966.Google Scholar
12. Hawkins, R. and Trevett, E. G. Changes in the flow at the base of a bluff body due to a disturbance in its wake. Presented at the AGARD Specialists’ Meeting on “Separated Flows”, Belgium, May 1966. Conference Proceedings 4, AGARD, Paris, 1966.Google Scholar
13. Page, R. H. and Przirembel, C. E. G. Experimental investigation of axisymmetric base flow. Rutgers—The State University, 113-ME-F, December 1966.Google Scholar
14. Przirembel, C. E. G. The turbulent near-wake of an axisymmetric body at supersonic speeds. PhD Thesis, Rutgers—The State University, 1967.Google Scholar
15. Martellucci, A. et al. Measurements of the turbulent near-wake of a cone at Mach 6. AIAA Paper No. 66-54, January 1966.Google Scholar
16. Sirieux, M. and Delery, J. Analyse expérimentale du proche sillage d’un corps élancé libre de tout support latéral. AGARD Conference Proceedings 19, Fluid Physics of Hypersonic Wakes, May 1967.Google Scholar