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The Flow Past Elliptic-nosed Cylinders and Bodies of Revolution in Supersonic Air Streams*

Published online by Cambridge University Press:  07 June 2016

D. W. Holder  and
A. Chinneck
D. W. Holder
Affiliation:
Aerodynamics Division, National Physical Laboratory
A. Chinneck
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

The flow past families of two-dimensional cylinders and bodies of revolution with elliptic noses at zero incidence has been examined at free stream Mach numbers between 1·42 and 1·82. The observations include schlieren photographs and measurements of the pressure distributions at the surface.

The measured pressure distributions and positions of the detached bow waves are found to be in fair agreement with values calculated by a number of methods. The drag coefficients of the slender two-dimensional elliptic noses are considerably higher than those calculated for wedges of the same axis ratio with attached shock waves, but the drags become almost equal when the axis ratio approaches the value for subsonic flow behind the bow wave of the wedge. For most axis ratios the drag coefficients of the elliptic-nosed bodies of revolution are lower than those for cones of the same axis ratio.

Type
Research Article
Information
Aeronautical Quarterly , Volume 4 , Issue 4 , February 1954 , pp. 317 - 340
Copyright
Copyright © Royal Aeronautical Society. 1954

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Footnotes

*

Some preliminary results of this investigation are described in A.R.C. 12, 418, 12, 660, 12, 495.

References

1. Holder, D. W. and North, R. J. (1949). The 9 in. x 3 in. N.P.L. Induced-Flow High speed Wind Tunnel. R. & M. 2781, 1949.Google Scholar
2. Holder, D. W., North, R. J. and Chinneck, A. (1950). Experiments with Static Tubes in a Supersonic Airstream. R. & M. 2782, 1950.Google Scholar
3. North, R. J. and Holder, D. W. (1949). A Spark Light Source for Schlieren and Direct-shadow Photography. Unpublished N.P.L. Report, 1949.Google Scholar
4. Holder, D. W. and North, R. J. (1950). The Toepler-Schlieren Apparatus. R. & M. 2780, 1950.Google Scholar
5. Ferri, A. (1942). Influenza del Numero di Reynolds ai Grandi Numeri di Mach. Atti di Guidonia 67, 68 and 69, 1942. See also The Influence of the Reynolds Number at Large Mach numbers. Eula, A. (L'Aerotecnica, Vol. XX, No. 1, Jan. 1940, pp. 20–29). Translated by Flint., M. Air Ministry Translation No. 1015. A.R.C. 4469, F.M. 449.Google Scholar
6. Maccoll, J. W. and Codd, J. (1945). Theoretical Investigations of the Flow around various Bodies in the Sonic Region of Velocities. A.R.C. 9315, 1945.Google Scholar
7. Liepmann, H. W. and Bryson, A. E. (1950). Transonic Flow Past Wedge Sections. Journal of the Aeronautical Sciences, December 1950.Google Scholar
8. Heberle, J. W., Wood, G. P. and Gooderum, P. B. (1950). Data on Shape and Location of Detached Shock Waves on Cones and Spheres. N.A.C.A. T.N. 2000, 1950.Google Scholar
9. Holder, D. W., Chinneck, A. and North, R. J. (1950). Pressure Measurements in a Supersonic Tunnel on a Two-dimensional Aerofoil of R.A.E. 104 Section. A.R.C. Current Paper No. 62, 1950.Google Scholar
10. Holder, D. W. and North, R. J. (1950). Observations of the Interaction Between the Shock Waves and Boundary Layers at the Trailing Edges of Aerofoils in Supersonic Flow. A.R.C. Current Paper No. 53, 1950.Google Scholar
11. Beastall, D. and Pallant, R. J. (1950). Wind Tunnel Tests on Two-dimensional Supersonic Aerofoils at M= 186 and M=248. R. & M. 2800, 1950.Google Scholar
12. Holder, D. W., Chinneck, A. and Hurley, D. G. (1950). Observations of the Supersonic Flow Round a 6 per cent, thick Double Wedge. A.R.C. Current Paper No. 63, 1950.Google Scholar
13. Hilton, W. F. (1946). Force Coefficients on Round Nosed Aerofoils at Supersonic Speeds. A.R.C. 9756, 1946.Google Scholar
14. Mair, W. A. (1947). A Note on Hilton's Empirical Method of Calculating Pressure Distributions on Round Nosed Aerofoils at Supersonic Speeds. A.R.C. 10, 719, 1947.Google Scholar
15. Moeckel, W. E. (1949). Approximate Method for Predicting Form and Location of Detached Shock Waves ahead of Plane or Axially Symmetric Bodies. N.A.C.A. T.N. 1921, 1949.Google Scholar
16. Busemann, A. (1949). A Review of Analytical Methods for the Treatment of Flows with Detached Shocks. N.A.C.A. T.N. 1858, 1949.Google Scholar