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Transonic Similarity Correlation of the Terminal Shock Jump on Aerofoils

Published online by Cambridge University Press:  04 July 2016

D. G. Mabey
D. G. Mabey*
Affiliation:
Royal Aircraft Establishment, Bedford
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Extract

This note illustrates the correlation of the pressure distributions measured on three NACA 16-series aerofoils at subsonic and transonic speeds. The transonic similarity parameters proposed by Spreiter

are used for the subsonic, transonic and supersonic types of flow illustrated in Fig. 1.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 639 , March 1964 , pp. 199 - 203
Copyright
Copyright © Royal Aeronautical Society 1964

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References

1.Ladson, C. L. Chordwise Pressure Distributions Over Several NACA 16-Series Aerofoils at Transonic Mach Numbers up to 1-25. NASA TIL 6454. NASA Memo 6-1-59L, June 1959.Google Scholar
2.Spreiter, J. R.On Alternative Forms for the Basic Equations of Transonic Flow Theory. Journal of the Aeronautical Sciences, Vol. 21(1), p. 10, 1954.Google Scholar
3.Sinnott, C. S. and Osbourne, J. Review and Extension of Transonic Aerofoil Theory. ARC 20459. 20460, 20461. R&M 3156, 1961.Google Scholar
4.Spreiter, J. R., Alksne, A. Y. and Hyett, B. J. Theoretical Pressure Distributions for Several Related Non-Lifting Aerofoils at High Subsonic Speeds. NACA TN 4148, January 1958.Google Scholar
5.Mabey, D. G.Leading-Edge Attachment in Transonic Flow With Laminar or Turbulent Boundary Layers. Journal of the Aerospace Sciences, Vol. 29(9), p. 1034, 1962.Google Scholar