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Two-Dimensional Aft Bodies for Minimum Pressure Drag in Supersonic Flow

Published online by Cambridge University Press:  07 June 2016

P R Viswanath  and
R Narasimha
P R Viswanath
Affiliation:
Indian Institute of Science, Bangalore
R Narasimha
Affiliation:
Indian Institute of Science, Bangalore
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Summary

The base pressure correlation proposed earlier by the authors, to take into account the effects of the boundary layer and of the boat-tail angle, is utilised in the design of two-dimensional aft bodies for minimum drag in supersonic flow. The general advantages of boat-tailing are indicated and charts of optimum profile parameters and minimum drag are provided for use in preliminary design. The effects on aft-body drag of possible reversion of the boundary layer at a sudden expansion are discussed, and the relevance of the optimum shapes found to the lifting case is indicated. The calculated optimum geometry is in good agreement with the experimental results of Fuller and Reid.

Type
Research Article
Information
Aeronautical Quarterly , Volume 27 , Issue 4 , November 1976 , pp. 263 - 269
Copyright
Copyright © Royal Aeronautical Society. 1976

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References

1 Chapman, D R Reduction of profile drag at supersonic velocities by the use of airfoil sections having blunt trailing edge, NACA TN 3503, 1955.Google Scholar
2 Chapman, DR Rester, R H Effect of trailing edge thickness on lift at supersonic velocities. NACA TN 3504, 1955.Google Scholar
3 Tanner, M Experimental investigation of drag of wings with blunt trailing edge at transonic speeds. AGARD Conference Proceedings 83 on Facilities and Techniques for Aerodynamic Testing at Transonic Speeds at High Reynolds Number, 1971.Google Scholar
4 Lichtfuss, H J Starken, H Supersonic cascade flow. Progress in Aerospace Sciences, Vol 15, p 37, Pergamon, 1974.Google Scholar
5 Chapman, DR Airfoil profiles for minimum pressure drag at supersonic velocities – General analysis with application to linearized supersonic flow. NACA Report 1063, 1952.Google Scholar
6 Pritchard, RE Optimum airfoils at moderate supersonic speeds, Part 5–Minimum drag, including base drag. Aero. Astronautics Report 45, Rice University, 1968.Google Scholar
7 Chapman, DR Wimbrow, W R Rester, R H Experimental investigation of base pressure on blunt trailing edge wings at supersonic velocities. NACA Report 1109, 1952.Google Scholar
8 Kraiko, AN Tagirov, R N Optimal two-dimensional afterbody at supersonic speeds. Fluid Dynamics (English), Consultants Bureau, New York, Vol 6, p 403, 1973.Google Scholar
9 Korst, H H A theory of base pressures in transonic and supersonic flow. Journal of Applied Mechanics, Vol 23, p 593, 1956.CrossRefGoogle Scholar
10 Viswanath, P R Narasimha, R Two-dimensional boat-tailed bases in supersonic flow. Aeronautical Quarterly, Vol XXV, p 210, 1974.Google Scholar
11 Narasimha, R Viswanath, P R Reverse transition at an expansion corner in supersonic flow. AIAA Journal, Vol 13, p 693, 1975.CrossRefGoogle Scholar
12 Miele, Angelo (Editor) Theory of Optimum Aerodynamic Shapes, Academic Press, 1965.Google Scholar
13 Viswanath, P R Two-dimensional boat-tailed bases and design for minimum drag in supersonic flow. PhD thesis, Department of Aeronautical Engineering, Indian Institute of Science, Bangalore, 1975.Google Scholar
14 Pritchard, R E Optimum airfoils at moderate supersonic speeds. Part 6 – Base drag effects on maximum lift to drag ratio for given thickness. Aero. Astronautics Report 46, Rice University, 1968.Google Scholar
15 Nash, J F A discussion of two-dimensional turbulent base flows. ARC R & M 3468, 1967.Google Scholar
16 Hopkins, E J Jillie, D W Serensen, V L Charts for estimating boundary layer transition on flat plates, NASA TN-D 5846, 1970.Google Scholar
17 Deem, R E Murphy, J S Flat plate boundary layer transition at hypersonic speeds. AIAA Paper 65–128, 1965.Google Scholar
18 Fuller, L Reid, J Experiments on two-dimensional base flow at M = 2.4. ARC R & M 3064, 1958.Google Scholar