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Studies of vortex flaps for different sweepback angle delta wings

Published online by Cambridge University Press:  04 July 2016

K. Rinoie
K. Rinoie*
Affiliation:
Department of Aeronautics and AstronauticsUniversity of TokyoTokyo, Japan
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Abstract

Low speed windtunnel measurements were made on a 50° delta wing with leading edge vortex flaps. Improvements in the lift/drag ratio were obtained by deflecting the leading edge vortex flap. Comparisons were made between the previously measured 60° and 70° delta wing results and the present 50° wing results. Improvements in the lift/drag ratio of the 50° delta wing were attained over a wider lift coefficient range than for the 70° delta wing. The highest lift/drag ratio for the 50° delta wing is achieved when the flow attaches to the flap surface without any large area of separation. Estimations of the aerodynamic forces were also made using a quasi-vortex lattice method coupled with the leading edge suction analogy for the 50°, 60° and 70° delta wings. The results obtained from this analysis agree qualitatively with the experimental results.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1009 , November 1997, pp. 409 - 416
Copyright
Copyright © Royal Aeronautical Society 1997 

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References

1. Rao, D.M. Leading edge vortex-flap experiments on a 74° delta wing, NASACR-159161, 1979.Google Scholar
2. Campbeli, J.F. and Osborn, R.F. Leading edge vortex research: some nonplanar concepts and current challenges, Vortex Flow Aerodynamics Vol I, NASA CP-2416, 1986, pp 31–63.Google Scholar
3. Rinoie, K. Experiments on a 60° delta wing with vortex flaps and vortex plates, Aeronaut J, January 1993, 97, (961), pp 33–38.Google Scholar
4. Rinoie, K. and Stollery, J.L. Experimental studies of vortex flaps and vortex plates, J Aircr, March-April 1994, 31, pp 322–329.Google Scholar
5. Rinoie, K., Fujita, T., Iwasaki, A. and Fujieda, H. Studies on the optimum flap deflection angle of vortex flaps, Proceedings of the 19th ICAS Conference, September 1994, ICAS-94-4.5.4.Google Scholar
6. Rinoie, K. Estimating the aerodynamic characteristics of vortex flaps using the leading edge suction analogy, Trans Japan Soc, Aero & Space Sci, November 1993, 36, (113), pp 143–152.Google Scholar
7. Rom, J. High Angle of Attack Aerodynamics, Springer-Verlag, New York, 1991, pp 15–21.Google Scholar
8. Polhamus, E.C. A Concept of the vortex lift of sharp-edge delta wings based on a leading edge suction analogy, NASA TN D-3767, 1966.Google Scholar
9. Lan, C.E. A Quasi-vortex-lattice method in thin wing theory, J Aircr, September 1974, 11, pp 518–527.Google Scholar
10. Lamar, J.E., Schemensky, R.T. and Reddy, C.S. Development of a vortex-lift design procedure and application to a slender manoeuvrewing configuration, J Aircr, April 1981, 18, pp 259–266.Google Scholar
11. Lan, C.E. and Chang, J. Calculation of Vortex Lift Effect for Cambered Wings by the Suction Analogy, NASA CR-3449, 1981.Google Scholar