CLARK W AIRFOIL 17. 17. 0.000000 0.000000 0.012500 0.021990 0.025000 0.031170 0.050000 0.044440 0.075000 0.054520 0.100000 0.062490 0.150000 0.074940 0.200000 0.083080 0.300000 0.090470 0.400000 0.090560 0.500000 0.085950 0.600000 0.076740 0.700000 0.063230 0.800000 0.045820 0.900000 0.025210 0.950000 0.013550 1.000000 0.001000 0.000000 0.000000 0.012500 -0.016110 0.025000 -0.020530 0.050000 -0.025760 0.075000 -0.028280 0.100000 -0.029310 0.150000 -0.029470 0.200000 -0.027920 0.300000 -0.021730 0.400000 -0.015440 0.500000 -0.012850 0.600000 -0.012360 0.700000 -0.012070 0.800000 -0.009480 0.900000 -0.005490 0.950000 -0.002850 1.000000 0.000000