Stokely, 1504 North Horseshoe Circle, Virginia Beach, VA, 23451, U.S.A., July 1984. S., The Design of Airfoils at Low Reynolds Numbers, Soartech #3, published by H. and Pope, A., Low-Speed Wind Tunnel Testing, John Wiley & Sons, second ed., 1984. E., Hot-Wire Anemometry, Oxford University Press, 1982.įraser, D.B., private communications, 1989. Stokely, 1504 North Horseshoe Circle, Virginia Beach, VA, 23451, U.S.A., July 1989. F., and Fraser, D., Airfoils at Low Speeds, Soartech #8, published by H. B., “ISES: A Two-Dimensional Viscous Aerodynamic Design and Analysis Code,” AIAA Paper 87–0424, January 1987. B., “Viscous-Inviscid Analysis of Transonic and Low-Reynolds Number Airfoils,” AIAA J., Vol. M., “A Computer Program for the Design and Analysis of Low-Speed Airfoils, Including Transition,” NASA TM 80210, August 1980.ĭrela, M. M., “Airfoil Design for Reynolds Numbers Between 50,000 and 500,000,” Proceedings of the Conference on Low Reynolds Number Airfoil Aerodynamics, Notre Dame, Indiana, June 1986.Įppler, R. W., “Some Research on Two-Dimensional Laminar Separation Bubbles,” AGARD CP-102, Paper 2, Lisbon, 1972.Įppler, R. M., “Aerodynamics at Low Reynolds Numbers: A Review of Theoretical and Experimental Research at Delft University of Technology,” Aerodynamics at Low Reynolds Numbers 104 Re 106 International Conference, London, October 1986.ĭobbinga, E., van Ingen, J. This process is experimental and the keywords may be updated as the learning algorithm improves. These keywords were added by machine and not by the authors. The effects of model inaccuracies are also discussed, as well as the importance of a thin trailing edge in achieving low drag. Several types of trips were compared (zig-zag trips, bump tape, blowing, and two-dimensional trips), and the simple two-dimensional trip was found to yield the greatest improvement. Boundary layer trips were also investigated as a means of reducing drag. Several of the new airfoils show significant performance improvements over previous airfoils. The design philosophy is discussed and verified experimentally. Seventeen of the most promising designs were actually wind tunnel tested. Based on the results of over 40 airfoils tested during the first phase of this program (including the DAE51, FX63–137, E205, E374, E214, E387, Miley, NACA 0009, S3021, S2091, S4233), several new airfoils were designed using the Eppler and Somers code and screened using the Drela and Giles ISES code. Comparisons of data obtained in the Princeton facility with that in several others are presented and show good agreement. Lift and Drag data were taken at chord Reynolds numbers between 0.6 × 10 5 and 3.0 × 10 5. The experimental facility and measurement technique are discussed in detail, and turbulence measurements in the tunnel freestream are presented. Both experimental and computational techniques were used. This paper focuses on the development of efficient low Reynolds number airfoils.
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