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Theory of transonic shear flow past a thin aerofoil

Published online by Cambridge University Press:  29 March 2006

Masanobu Namba
Masanobu Namba
Affiliation:
Department of Aeronautical Engineering, Kyushu University, Fukuoka, Japan
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Abstract

A generalized linear theory is developed for a compressible shear flow by extending the Fourier integral representations for the pressure field disturbed by pressure dipoles, and it is applied to a transonic shear flow past a thin aerofoil.

A method of determining the pressure distribution on the aerofoil surface is shown. Some numerical examples are presented and discussed.

It is found that the three-dimensional effect due to non-uniformity of the Mach number appears in the greatest degree at lower supersonic span-stations. Even within the scope of the linearized theory not such a great lift force arises near the sonic station as would be expected from the linearized uniform flow theory.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 36 , Issue 4 , 19 May 1969 , pp. 759 - 783
Copyright
© 1969 Cambridge University Press

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References

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Mccune, J. E. 1958 J. Aeron. Space Sci. 25, 616.
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Namba, M. 1969 J. Fluid Mech. 36, 735.
Namba, M. & Asanuma, T. 1965 Trans. Japan Soc. Mech. Engrs 31, 1236 (in Japanese); Bull. Inst. Space Aeron. Sci. Univ. Tokyo, 1, 164 (in Japanese).
Namba, M. & Asanuma, T. 1967 Bull. Japan Soc. Mech. Engrs 10, 920; Rep. of Inst. Space Aeron. Sci. Univ. Tokyo, 32, 133.