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Design Charts for Estimating Turbulent Skin Friction Drag on Cylindrical Bodies with Tangent Parabolic or Ogival Fore-Bodies at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

R. A. Brewer  and
M. W. R. Seel
R. A. Brewer
Affiliation:
Guided Weapons Department, Bristol Aircraft Ltd
M. W. R. Seel
Affiliation:
Guided Weapons Department, Bristol Aircraft Ltd
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Extract

When estimating the skin friction drag on bodies of revolution at the project design stage, it is normal practice to use an “equivalent flat-plate” method. This calculation is simple and requires little time to perform. However, in the final design stage, when more accurate estimates of the skin friction drag should be made the “equivalent flat-plate” method is still used. More exact methods, which include pressure gradient effects, are very laborious if they are evaluated by hand calculators. Even if a digital computor is used to evaluate the more exact methods, the time required to perform the calculations is considerably longer than that taken to calculate the other forms of drag. For these reasons, the simple “flat-plate” method has long held favour with designers.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 66 , Issue 615 , March 1962 , pp. 196 - 199
Copyright
Copyright © Royal Aeronautical Society 1962

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References

1.Seel, M. W. R. and Brewer, R. A. (1961). On the Calculation of Turbulent Skin Friction Drag on Some Bodies of Revolution at Supersonic Speeds. Bristol Aircraft Ltd. Tech. Report No. 74. August 1961.Google Scholar
2.Spence, D. A. (1959). The Growth of Compressible Turbulent Boundary Layers on Isothermal and Adiabatic Walls. R.A.E. Report No. Aero. 2619. June 1959.Google Scholar