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.
Wind-Tunnel Results for an Improved 21-Percent-Thick Low-Speed Airfoil Section
1978
47 pages
Report
No indication
English