XFOIL Version 6.96 Calculated polar for: CLARK YM-18 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.8554 0.08325 0.07946 -0.0806 1.0000 0.0385 -17.500 -0.8861 0.07496 0.07098 -0.0860 1.0000 0.0386 -17.250 -0.9064 0.06853 0.06440 -0.0901 1.0000 0.0387 -17.000 -0.9217 0.06308 0.05882 -0.0935 1.0000 0.0389 -16.750 -0.9336 0.05828 0.05389 -0.0964 1.0000 0.0391 -16.500 -0.9433 0.05399 0.04947 -0.0989 1.0000 0.0393 -16.250 -0.9510 0.05014 0.04550 -0.1009 1.0000 0.0396 -16.000 -0.9571 0.04674 0.04199 -0.1023 1.0000 0.0398 -15.750 -0.9622 0.04377 0.03890 -0.1032 1.0000 0.0400 -15.500 -0.9674 0.04115 0.03618 -0.1033 1.0000 0.0403 -15.250 -0.9734 0.03891 0.03383 -0.1025 1.0000 0.0405 -15.000 -0.9808 0.03699 0.03182 -0.1009 1.0000 0.0407 -14.750 -0.9911 0.03542 0.03016 -0.0982 1.0000 0.0408 -14.500 -1.0056 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0.6311 0.5877 0.000 0.3833 0.00847 0.00303 -0.0746 0.6214 0.6618 0.250 0.4062 0.00836 0.00308 -0.0734 0.6124 0.7213 0.500 0.4302 0.00831 0.00315 -0.0724 0.6025 0.7671 0.750 0.4546 0.00831 0.00322 -0.0714 0.5931 0.8027 1.000 0.4792 0.00835 0.00329 -0.0704 0.5824 0.8333 1.250 0.5039 0.00841 0.00339 -0.0695 0.5720 0.8602 1.500 0.5283 0.00852 0.00348 -0.0685 0.5605 0.8834 1.750 0.5536 0.00863 0.00359 -0.0677 0.5484 0.9035 2.000 0.5789 0.00879 0.00371 -0.0669 0.5355 0.9213 2.250 0.6047 0.00899 0.00384 -0.0663 0.5206 0.9364 2.500 0.6310 0.00921 0.00398 -0.0658 0.5038 0.9500 2.750 0.6606 0.00948 0.00415 -0.0661 0.4849 0.9613 3.000 0.6943 0.00977 0.00433 -0.0673 0.4632 0.9688 3.250 0.7277 0.01010 0.00454 -0.0686 0.4390 0.9763 3.500 0.7643 0.01049 0.00477 -0.0707 0.4152 0.9813 3.750 0.8027 0.01088 0.00502 -0.0732 0.3960 0.9858 4.000 0.8409 0.01125 0.00528 -0.0757 0.3817 0.9919 4.250 0.8843 0.01159 0.00553 -0.0792 0.3704 0.9956 4.500 0.9254 0.01192 0.00577 -0.0823 0.3616 0.9994 4.750 0.9403 0.01213 0.00593 -0.0800 0.3560 1.0000 5.000 0.9511 0.01225 0.00605 -0.0768 0.3515 1.0000 5.250 0.9601 0.01241 0.00619 -0.0732 0.3469 1.0000 5.500 0.9658 0.01261 0.00634 -0.0690 0.3423 1.0000 5.750 0.9721 0.01280 0.00650 -0.0648 0.3382 1.0000 6.000 0.9847 0.01292 0.00664 -0.0619 0.3345 1.0000 6.250 0.9991 0.01312 0.00683 -0.0594 0.3304 1.0000 6.500 1.0145 0.01340 0.00706 -0.0572 0.3259 1.0000 6.750 1.0307 0.01378 0.00738 -0.0553 0.3211 1.0000 7.000 1.0512 0.01396 0.00760 -0.0541 0.3179 1.0000 7.250 1.0715 0.01420 0.00786 -0.0529 0.3141 1.0000 7.500 1.0908 0.01450 0.00815 -0.0516 0.3100 1.0000 7.750 1.1091 0.01490 0.00849 -0.0502 0.3056 1.0000 8.000 1.1293 0.01524 0.00884 -0.0491 0.3019 1.0000 8.250 1.1504 0.01550 0.00914 -0.0482 0.2989 1.0000 8.500 1.1712 0.01580 0.00947 -0.0473 0.2957 1.0000 8.750 1.1911 0.01616 0.00983 -0.0463 0.2922 1.0000 9.000 1.2096 0.01660 0.01025 -0.0451 0.2885 1.0000 9.250 1.2290 0.01705 0.01068 -0.0441 0.2849 1.0000 9.500 1.2496 0.01736 0.01107 -0.0433 0.2820 1.0000 9.750 1.2697 0.01773 0.01148 -0.0424 0.2785 1.0000 10.000 1.2887 0.01816 0.01192 -0.0415 0.2749 1.0000 10.250 1.3059 0.01870 0.01244 -0.0403 0.2710 1.0000 10.500 1.3240 0.01921 0.01298 -0.0393 0.2672 1.0000 10.750 1.3437 0.01963 0.01346 -0.0386 0.2633 1.0000 11.000 1.3617 0.02014 0.01401 -0.0377 0.2587 1.0000 11.250 1.3772 0.02080 0.01466 -0.0365 0.2542 1.0000 11.500 1.3943 0.02141 0.01531 -0.0356 0.2498 1.0000 11.750 1.4126 0.02196 0.01591 -0.0348 0.2447 1.0000 12.000 1.4272 0.02273 0.01668 -0.0337 0.2391 1.0000 12.250 1.4423 0.02349 0.01748 -0.0327 0.2335 1.0000 12.500 1.4576 0.02426 0.01828 -0.0318 0.2264 1.0000 12.750 1.4693 0.02529 0.01929 -0.0306 0.2191 1.0000 13.000 1.4826 0.02624 0.02027 -0.0297 0.2102 1.0000 13.250 1.4924 0.02745 0.02147 -0.0285 0.2012 1.0000 13.500 1.4987 0.02894 0.02292 -0.0271 0.1910 1.0000 13.750 1.5058 0.03043 0.02440 -0.0259 0.1804 1.0000 14.000 1.5103 0.03217 0.02612 -0.0246 0.1704 1.0000 14.250 1.5119 0.03418 0.02810 -0.0232 0.1610 1.0000 14.500 1.5121 0.03638 0.03028 -0.0219 0.1520 1.0000 14.750 1.5151 0.03842 0.03232 -0.0209 0.1438 1.0000 15.000 1.5136 0.04091 0.03480 -0.0198 0.1369 1.0000 15.250 1.5155 0.04316 0.03707 -0.0190 0.1306 1.0000 15.500 1.5126 0.04593 0.03985 -0.0181 0.1255 1.0000 15.750 1.5159 0.04817 0.04214 -0.0176 0.1212 1.0000 16.000 1.5138 0.05099 0.04498 -0.0170 0.1174 1.0000 16.250 1.5110 0.05394 0.04797 -0.0166 0.1142 1.0000 16.500 1.5134 0.05642 0.05052 -0.0163 0.1114 1.0000 16.750 1.5123 0.05933 0.05349 -0.0161 0.1089 1.0000 17.000 1.5075 0.06268 0.05688 -0.0160 0.1065 1.0000 17.250 1.5000 0.06636 0.06059 -0.0160 0.1043 1.0000 17.500 1.5025 0.06899 0.06332 -0.0160 0.1026 1.0000 17.750 1.5017 0.07204 0.06644 -0.0162 0.1008 1.0000 18.000 1.4986 0.07539 0.06986 -0.0165 0.0991 1.0000 18.250 1.4935 0.07898 0.07351 -0.0169 0.0974 1.0000 18.500 1.4861 0.08288 0.07744 -0.0173 0.0958 1.0000 18.750 1.4806 0.08657 0.08117 -0.0178 0.0943 1.0000