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An Analysis of the Turbulent Base Pressure Problem in Supersonic Axisymmetric Flow

Published online by Cambridge University Press:  07 June 2016

H. McDonald
H. McDonald*
Affiliation:
British Aircraft Corporation (Operating) Limited, Preston Division
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Summary

The problem of predicting the turbulent supersonic base pressure in axisymmetric flow is treated by an extension of a method of solution to the two-dimensional problem given in Ref. 1. The solution consists principally in tracing the boundary-layer development from upstream of the base to downstream of the recompression region for a given base pressure. A unique solution is obtained by specifying the shape of the rehabilitated boundary-layer velocity profile.

A comparison with experiment in the case of the step-down cylinder problem (the sting-support problem) yields some very favourable results. It is pointed out that, while it has not been found possible to obtain a solution to the problem of a vanishingly small sting, the base pressure does not vary appreciably while the sting is decreased from about 0-3 of the base diameter down to zero. It would appear that the present analysis is capable of giving accurate results down to sting/diameter ratios of the order of 0·3.

Type
Research Article
Information
Aeronautical Quarterly , Volume 16 , Issue 2 , May 1965 , pp. 97 - 121
Copyright
Copyright © Royal Aeronautical Society. 1965

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References

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