Patent ID: 6607164
Filing Date: 2003-08-19
Classification: B64C

Abstract:
An airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, and a chord line, said airfoil providing primarily turbulent flow across said upper surface of said airfoil at the maximum lift coefficient, said airfoil having lift characteristics substantially insensitive to surface roughness on said leading edge, said airfoil having upper and lower surfaces defined at x/c locations on the chord line and the y/c distances from the chord line to points on the upper or lower surfaces, wherein the x/c locations and y/c distances correspond substantially to the following table:Upper SurfaceLower Surfacex/cy/cx/cy/c0.000010.000390.00009âˆ’0.001470.000170.002170.00054âˆ’0.003080.003570.011220.00151âˆ’0.004540.011170.021280.00300âˆ’0.006000.022810.031600.01018âˆ’0.010650.038450.041660.02452âˆ’0.016600.058030.050910.04424âˆ’0.022430.081810.058870.06896âˆ’0.028110.110190.065620.09830âˆ’0.033570.142970.071630.13180âˆ’0.038760.179540.077040.16902âˆ’0.043570.219370.081780.20943âˆ’0.047910.261910.085780.25250âˆ’0.051660.306620.088920.29769âˆ’0.054670.352960.091090.34441âˆ’0.056780.400370.092150.39208âˆ’0.057760.448280.091940.44011âˆ’0.057360.496140.090130.48787âˆ’0.054950.543790.086200.53570âˆ’0.049550.591590.080250.58486âˆ’0.041520.639460.072990.63544âˆ’0.032520.686780.065020.68645âˆ’0.023710.732900.056720.73682âˆ’0.015720.777150.048420.78548âˆ’0.009000.818850.040360.83135âˆ’0.003770.857320.032720.87343âˆ’0.000180.891910.025530.910730.001800.924090.018640.942280.002380.950970.012790.967340.001990.972220.008120.985440.001150.987590.004740.996360.000340.996890.002691.000000.000001.000000.00200