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Interference Between a Wing and a Surface of Velocity Discontinuity

Published online by Cambridge University Press:  07 June 2016

Norio Inumaru
Norio Inumaru*
Affiliation:
National Aerospace Laboratory, Tokyo
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Summary

A study is made on the aerodynamic interference between a wing and a surface of velocity discontinuity in a non-uniform potential flow field. Actually, the surface of velocity discontinuity is deformed around the wing, which penetrates the surface, but no theoretical predictions of the surface deformation can be found in existing papers. In the present paper, a deformation of the surface is theoretically predicted, leading to the conclusion that a “sectorial region” will be formed on the wing. Formation of the sectorial region is recognised in new experiments and in many existing experimental results. Both theoretical and experimental analyses are made of the physical roles of the sectorial region.

Type
Research Article
Information
Aeronautical Quarterly , Volume 24 , Issue 3 , August 1973 , pp. 192 - 206
Copyright
Copyright © Royal Aeronautical Society. 1973

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References

1 Koning, C Influence of the propeller on other parts of the airplane structure. Aerodynamic Theory, edited by Durand, W F, Vol IV, Springer, Berlin, 1935.Google Scholar
2 Ribner, H S Ellis, N D Theory and computer study of a wing in a slipstream. AIAA Paper 66-466, 1966.Google Scholar
3 Squire, H B Chester, W Calculation of the effect of slipstream on lift and induced drag. ARC R & M 2368, 1950.Google Scholar
4 Graham, E W Lagerstrom, P A Licher, R M Bean, B J A preliminary theoretical investigation of the effects of propeller slipstream on wing lift. Douglas Aircraft Report SM-14991, 1953.Google Scholar
5 Vandrey, F Beitrag zur Theorie des Tragflügels in schwach inhomogener, paralleler Strömung. Zeitschrift fur Angewandte Mathematik und Mechanik, Vol 20, p 148, 1940.Google Scholar
6 Schlichting, H Experimentelle Untersuchungen uber den Tragflügel in inhomogener Strömung. Jahrbuch der deutschen Luftfahrtforschung 1, 81, 1940.Google Scholar
7 von Kármán, Th Tsien, H S Lifting-line theory for a wing in non-uniform flow. Quarterly of Applied Mathematics. Vol. 3, p 1, 1945.Google Scholar
8 Inumaru, N et al Wind tunnel investigations of the STOL airplane with attention to the relations between the aerodynamic characteristics and the wake structure. National Aerospace Laboratory of Japan, NAL TR-197T, May 1970.Google Scholar
9 Lomax, H Heaslet, M Fuller, F B Integrals and integral equations in linearized wing theory. NACA Report 1954, 1950.Google Scholar
10 Sweberg, H H The effect of propeller operation on the air flow in the region of the tailplane for a twin-engine tractor monoplane. NACA WR L-381, 1942.Google Scholar
11 Stuper, J Einfluss des Schraubenstrahls auf Flügel und Leitwerk. Luftfahrtforschung, Vol 15, No 4, 1938,Google Scholar
12 Brenckmann, M Experimental investigation of the aerodynamics of a wing in a slipstream. Journal of the Aeronautical Sciences, May 1958.Google Scholar