XFOIL Version 6.94 Calculated polar for: WASP (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4016 0.00714 0.00233 -0.0835 0.7719 1.0000 0.500 0.4515 0.00738 0.00226 -0.0817 0.7270 1.0000 1.000 0.5007 0.00767 0.00226 -0.0798 0.6821 1.0000 1.500 0.5494 0.00801 0.00231 -0.0779 0.6374 1.0000 2.000 0.5980 0.00836 0.00243 -0.0760 0.5931 1.0000 2.500 0.6464 0.00877 0.00260 -0.0742 0.5524 1.0000 3.000 0.6952 0.00919 0.00285 -0.0724 0.5152 1.0000 3.500 0.7441 0.00963 0.00313 -0.0708 0.4805 1.0000 4.000 0.7930 0.01009 0.00348 -0.0692 0.4489 1.0000 4.500 0.8418 0.01055 0.00386 -0.0676 0.4171 1.0000 5.000 0.8907 0.01104 0.00432 -0.0661 0.3874 1.0000 5.500 0.9388 0.01159 0.00481 -0.0645 0.3567 1.0000 6.000 0.9862 0.01221 0.00537 -0.0628 0.3273 1.0000 6.500 1.0327 0.01290 0.00602 -0.0610 0.2964 1.0000 7.000 1.0784 0.01357 0.00664 -0.0591 0.2566 1.0000 7.500 1.1233 0.01437 0.00742 -0.0572 0.2231 1.0000 8.000 1.1673 0.01524 0.00826 -0.0552 0.1906 1.0000 8.500 1.2098 0.01624 0.00924 -0.0531 0.1556 1.0000 9.000 1.2433 0.01805 0.01067 -0.0499 0.0827 1.0000 9.500 1.2614 0.02120 0.01354 -0.0443 0.0386 1.0000 10.000 1.2864 0.02338 0.01590 -0.0397 0.0312 1.0000 11.000 1.3072 0.02879 0.02174 -0.0274 0.0247 1.0000 11.500 1.3133 0.03210 0.02523 -0.0225 0.0229 1.0000 12.000 1.3085 0.03707 0.03039 -0.0179 0.0212 1.0000 12.500 1.3135 0.04156 0.03518 -0.0152 0.0199 1.0000 13.000 1.3177 0.04641 0.04032 -0.0134 0.0188 1.0000 13.500 1.3170 0.05217 0.04641 -0.0123 0.0180 1.0000 14.000 1.3112 0.05887 0.05342 -0.0122 0.0173 1.0000 14.500 1.2998 0.06666 0.06152 -0.0133 0.0168 1.0000 15.000 1.2826 0.07568 0.07086 -0.0156 0.0165 1.0000 15.500 1.2598 0.08625 0.08177 -0.0194 0.0163 1.0000 16.000 1.2305 0.09877 0.09464 -0.0250 0.0162 1.0000 16.500 1.1935 0.11393 0.11018 -0.0330 0.0164 1.0000 17.000 1.1449 0.13330 0.12996 -0.0443 0.0168 1.0000