Experimental Investigation of Three Helicopter Rotor Airfoils Designed Analytically

摘要

Three helicopter rotor airfoils designed analytically have been investigated in a wind tunnel at Mach numbers from about 0.30 to 0.90 and Reynolds numbers from about 0.8 to 2.3 × lo6. The airfoils had thickness-to-chord ratios of 0.08, 0.10, and 0.12 with maximum thickness at 40 percent chord. The camber distri¬bution of each section was the same with maximum camber at 35 percent chord. The 10-percent-thick airfoil was also investigated at Reynolds numbers from 4.8 × 105 to 9.4 × 106.