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Preliminary Results of Some Experiments with a Vortex Augmented Wing
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English
Abstract
A wind tunnel investigation was made of a new high-lift system consisting of a leading edge cusp flap combined with split upper and lower trailing edge flaps. The idea behind the system was to generate two strong spanwise vortices that would increase maximum lift and drag simultaneously. Test results were not encouraging. The spanwise vortices were observed, but were not sufficiently strong to generate the anticipated high lift. Several interesting flow phenomena were observed and are described. The purpose of this paper is to present a summary of results obtained from this wind tunnel test program.
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Citation
Roskam, J. and Gleason, M., "Preliminary Results of Some Experiments with a Vortex Augmented Wing," SAE Technical Paper 720321, 1972, https://doi.org/10.4271/720321.Also In
References
- Gleason Mark E. “An Initial Three-Dimensional Wind Tunnel Investigation of a Vortex Augmented Wing.” University of Kansas 1971
- Gladych B. Michael unpublished work with glider installation of vortex augmented wing Issaquah, Washington
- The Boeing Company unpublished data concerning two-dimensional water table investigation of a vortex augmented wing Renton, Washington 1969
- Mandl P. “Effect of Standing Vortex on Flow About Suction Airfoils With Split Flaps.” National Aeronautical Establishment Ottawa 1959
- Sapp Charles W. “Experimental Investigation of the Effects of Spoilers on the Aerodynamic Characteristics of Light Aircraft.” University of Kansas 1969
- Young J. D. “A New Economical and Accurate Method of Building Wind Tunnel Models.” Flight Research Laboratory, University of Kansas Lawrence, Kansas 1969