The wind-tunnel test results of five airfoil sections with 28.57 % chord thickness at chord Reynolds number of 33000, 66000, and 99000 are presented. Lift and drag forces have been measured and flow visualizations have been made. It is shown by cutting off the trailing edge of the section and by making its trailing edge blunt at low Reynolds numbers that the total drag can be reduced, the maximum lift increased, the linearity of lift curve with incidences improved, and the maximum lift-to-drag ratio increased. The structural merits of blunt trailing-edge sections are also discussed.
Experimental research on blunt trailing-edge airfoil sections at low Reynolds numbers
Experimentelle Untersuchung von Tagflügelabschnitten mit abgestumpfter Hinterkante bei niedrigen Reynolds-Zahlen
AIAA Journal ; 33 , 11 ; 2001-2005
1995
5 Seiten, 13 Bilder, 16 Quellen
Article (Journal)
English
Experimental Research on Blunt Trailing-Edge Airfoil Sections at Low Reynolds Numbers
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