XFOIL Version 6.96 Calculated polar for: FX 38-153 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5461 0.09770 0.09291 -0.0503 0.9995 0.0214 -10.500 -0.5601 0.09067 0.08582 -0.0548 0.9976 0.0211 -10.250 -0.5785 0.08439 0.07945 -0.0583 0.9953 0.0207 -10.000 -0.5986 0.07895 0.07387 -0.0603 0.9926 0.0204 -9.750 -0.6197 0.07453 0.06930 -0.0602 0.9890 0.0202 -9.500 -0.6405 0.07088 0.06548 -0.0589 0.9855 0.0200 -9.250 -0.6591 0.06769 0.06209 -0.0570 0.9817 0.0199 -9.000 -0.6750 0.06456 0.05875 -0.0540 0.9772 0.0198 -8.750 -0.6824 0.06105 0.05496 -0.0520 0.9733 0.0198 -8.500 -0.6817 0.05724 0.05078 -0.0509 0.9699 0.0198 -8.250 -0.6830 0.05388 0.04706 -0.0484 0.9664 0.0196 -8.000 -0.6811 0.05067 0.04347 -0.0458 0.9628 0.0193 -7.750 -0.6711 0.04744 0.03979 -0.0442 0.9596 0.0191 -7.500 -0.6549 0.04448 0.03636 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0.0013 0.0817 0.9455 12.000 1.0870 0.03992 0.03166 0.0020 0.0714 0.9474 12.250 1.0947 0.04151 0.03334 0.0031 0.0642 0.9493 12.500 1.0978 0.04333 0.03519 0.0045 0.0591 0.9517 12.750 1.1026 0.04513 0.03716 0.0057 0.0544 0.9543 13.000 1.1043 0.04729 0.03942 0.0068 0.0508 0.9570 13.250 1.1056 0.04964 0.04188 0.0077 0.0479 0.9596 13.500 1.1090 0.05187 0.04433 0.0084 0.0450 0.9621 13.750 1.1101 0.05427 0.04690 0.0091 0.0427 0.9646 14.000 1.1099 0.05695 0.04972 0.0095 0.0411 0.9674 14.250 1.1086 0.05987 0.05275 0.0097 0.0399 0.9703 14.750 1.1092 0.06569 0.05897 0.0096 0.0379 0.9769 15.000 1.1084 0.06879 0.06225 0.0093 0.0370 0.9816 15.250 1.1063 0.07195 0.06558 0.0088 0.0363 0.9902 15.500 1.1050 0.07534 0.06914 0.0079 0.0356 0.9999 15.750 1.1049 0.07902 0.07299 0.0067 0.0350 0.9999 16.000 1.1044 0.08283 0.07695 0.0053 0.0345 0.9999 16.250 1.1037 0.08673 0.08100 0.0038 0.0340 0.9999 16.500 1.1027 0.09071 0.08512 0.0022 0.0336 0.9999 16.750 1.1018 0.09470 0.08924 0.0006 0.0331 0.9999 17.000 1.0997 0.09897 0.09364 -0.0013 0.0326 0.9999 17.250 1.0912 0.10461 0.09955 -0.0043 0.0323 0.9999 17.500 1.0806 0.11083 0.10602 -0.0079 0.0320 0.9999 17.750 1.0671 0.11785 0.11330 -0.0122 0.0318 0.9999 18.000 1.0514 0.12561 0.12129 -0.0172 0.0316 0.9999 18.250 1.0323 0.13451 0.13040 -0.0232 0.0317 0.9999 18.500 1.0074 0.14533 0.14143 -0.0305 0.0319 0.9999 18.750 0.9705 0.16016 0.15643 -0.0404 0.0323 0.9999