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On an Approximate Method of Calculating Pressures on Non-lifting Head Shapes at Supersonic Speeds

Published online by Cambridge University Press:  07 June 2016

H. K. Zienkiewicz
H. K. Zienkiewicz*
Affiliation:
Fluid Motion Laboratory, University of Manchester
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Summary

Slender-body theory is used to derive the ogive of curvature approximation for very slender, pointed, convex head shapes at supersonic speeds. Results of application of this approximation, together with the λ-method for circular arc ogives, to a variety of non-slender head shapes show very good agreement with the method of characteristics, van Dyke's second-order theory and experiment. Good agreement with the method of characteristics and with experiment is obtained even in cases when the stagnation pressure losses across the nose shock wave are not negligible.

Type
Research Article
Information
Aeronautical Quarterly , Volume 6 , Issue 1 , February 1955 , pp. 31 - 45
Copyright
Copyright © Royal Aeronautical Society. 1955

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References

1. Bolton Shaw, B. W. and Zienkiewicz, H. K. The Rapid, Accurate Prediction of Pressure on Non-lifting Ogival Heads of Arbitrary Shape, at Supersonic Speeds. A.R.C. Current Paper 154 (The English Electric Co. Report LA.t.034, June 1952).Google Scholar
2. Zienkiewicz, H. K. A Method for Calculating Pressure Distributions on Circular Arc Ogives at Zero Incidence at Supersonic Speeds, Using the Prandtl-Meyer Flow Relations. A.R.C. Current Paper 114 (The English Electric Co. Report LA.t.024, January 1952).Google Scholar
3. Ehret, D. M. Accuracy of Approximate Methods for Predicting Pressures on Pointed Non-lifting Bodies of Revolution in Supersonic Flow. N.A.C.A. T.N. 2764, August 1952.Google Scholar
4. Lighthill, M. J. Supersonic Flow Past Bodies of Revolution. R. & M. 2003, January 1945.Google Scholar
5. Van Dyke, M. D. A Study of Hypersonic Small Disturbance Theory. Journal of the Aeronautical Sciences, Vol. 21, No. 3, March 1954, pp. 179–186; also N.A.C.A. T.N. 3173, May 1954.Google Scholar
6. Ehret, D. M., Rossow, V. J. and Stevens, V. I. An Analysis of the Applicability of the Hypersonic Similarity Law to the Study of Flow About Bodies of Revolution at Zero Angle of Attack. N.A.C.A. T.N. 2250, December 1950.Google Scholar
7. Rossow, V. J. Applicability of the Hypersonic Similarity Rule to Pressure Distributions which include the Effects of Rotation for Bodies of Revolution at Zero Angle of Attack. N.A.C.A. T.N. 2399, June 1951.Google Scholar
8. Eggers, A. J. and Savin, R. C. Approximate Methods for Calculating the Flow About Non-lifting Bodies of Revolution at High Supersonic Airspeeds. N.A.C.A. T.N. 2579, December 1951.Google Scholar
9. Tables of Supersonic Flow Around Cones. Technical Report No. 1. Department of Electrical Engineering, Massachusetts Institute of Technology, 1947.Google Scholar
10. Van Dyke, M. D. First- and Second-order Theory of Supersonic Flow Past Bodies of Revolution. Journal of the Aeronautical Sciences, pp. 161–178, March 1951.Google Scholar
11. Jorgensen, L. H. Nose Shapes for Minimum Pressure Drag at Supersonic Mach Numbers. Journal of the Aeronautical Sciences, pp. 276–279, April 1954.Google Scholar
12. Zienkiewicz, H. K., Chinneck, A., Berry, C. J. and Peggs, P. J. Experiments at M=1·8 on Bodies of Revolution Having Ogival Heads. A.R.C. Current Paper 148, January 1953.Google Scholar
13. Marson, G. B., Keates, R. E. and Socha, W. An Experimental Investigation of the Pressure Distribution on Five Bodies of Revolution at Mach Numbers of 2·45 and 3·19. College of Aeronautics Report No. 79, April 1954.Google Scholar