NASA NASA-TM-78650
NASA NASA-TM-78650 1978-JAN-01 Wnd-tunnel results for an mproved 21-percent-thck low-speed arfol secton
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Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.