Abstract
This paper focuses on the development of efficient low Reynolds number airfoils. Both experimental and computational techniques were used. The experimental facility and measurement technique are discussed in detail, and turbulence measurements in the tunnel freestream are presented. Lift and Drag data were taken at chord Reynolds numbers between 0.6 × 105 and 3.0 × 105. Comparisons of data obtained in the Princeton facility with that in several others are presented and show good agreement. 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. Seventeen of the most promising designs were actually wind tunnel tested. The design philosophy is discussed and verified experimentally. Several of the new airfoils show significant performance improvements over previous airfoils. Boundary layer trips were also investigated as a means of reducing 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. The effects of model inaccuracies are also discussed, as well as the importance of a thin trailing edge in achieving low drag.
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© 1989 Springer-Verlag Berlin, Heidelberg
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Donovan, J.F., Selig, M.S. (1989). Low Reynolds Number Airfoil Design and Wind Tunnel Testing at Princeton University. In: Mueller, T.J. (eds) Low Reynolds Number Aerodynamics. Lecture Notes in Engineering, vol 54. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-84010-4_4
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DOI: https://doi.org/10.1007/978-3-642-84010-4_4
Publisher Name: Springer, Berlin, Heidelberg
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