XFOIL Version 6.96 Calculated polar for: FX 66-182 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 ------ -------- --------- --------- -------- -------- -------- -12.500 -0.3159 0.09744 0.09273 -0.0733 0.8915 0.0273 -12.250 -0.3210 0.08691 0.08204 -0.0826 0.8672 0.0270 -12.000 -0.3364 0.07715 0.07205 -0.0914 0.8422 0.0266 -11.500 -0.3805 0.06317 0.05751 -0.1023 0.8000 0.0262 -11.250 -0.3999 0.05836 0.05242 -0.1049 0.7833 0.0262 -11.000 -0.4166 0.05432 0.04808 -0.1063 0.7691 0.0261 -10.500 -0.4441 0.04775 0.04090 -0.1065 0.7459 0.0263 -10.250 -0.4541 0.04521 0.03803 -0.1050 0.7366 0.0264 -10.000 -0.4600 0.04281 0.03525 -0.1031 0.7284 0.0268 -9.750 -0.4590 0.04040 0.03240 -0.1015 0.7210 0.0272 -9.500 -0.4488 0.03840 0.03019 -0.1007 0.7137 0.0279 -9.250 -0.4345 0.03717 0.02886 -0.1001 0.7071 0.0293 -9.000 -0.4196 0.03572 0.02720 -0.0994 0.7003 0.0305 -8.750 -0.4034 0.03412 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0.9327 0.03339 0.02466 -0.0638 0.5080 0.7961 6.750 0.9614 0.03351 0.02488 -0.0641 0.5068 0.8049 8.250 0.8579 0.05345 0.04562 -0.0496 0.4594 1.0000 8.750 0.8748 0.05711 0.04937 -0.0490 0.4488 1.0000 9.000 0.8563 0.06154 0.05383 -0.0483 0.4386 1.0000 9.250 0.8776 0.06214 0.05450 -0.0482 0.4357 1.0000 9.500 0.9033 0.06230 0.05474 -0.0482 0.4338 1.0000 9.750 0.9312 0.06220 0.05472 -0.0481 0.4325 1.0000 10.250 0.9372 0.06678 0.05945 -0.0474 0.4188 1.0000 11.250 0.9616 0.07477 0.06780 -0.0463 0.3921 1.0000 11.500 0.9899 0.07423 0.06739 -0.0459 0.3900 1.0000 12.000 1.0092 0.07715 0.07054 -0.0453 0.3761 1.0000 12.250 1.0043 0.08032 0.07379 -0.0452 0.3651 1.0000 12.500 1.0421 0.07773 0.07135 -0.0444 0.3614 1.0000 13.000 1.0598 0.07965 0.07346 -0.0435 0.3361 1.0000 13.250 1.0736 0.08006 0.07397 -0.0431 0.3211 1.0000 13.500 1.0868 0.08079 0.07477 -0.0428 0.3042 1.0000 13.750 1.0961 0.08230 0.07634 -0.0427 0.2859 1.0000 14.000 1.1074 0.08360 0.07767 -0.0425 0.2663 1.0000 14.250 1.1370 0.08182 0.07565 -0.0414 0.2301 1.0000 14.500 1.1400 0.08396 0.07747 -0.0411 0.1917 1.0000 14.750 1.1320 0.08788 0.08111 -0.0414 0.1583 1.0000 15.000 1.1225 0.09225 0.08529 -0.0420 0.1310 1.0000 15.250 1.1135 0.09672 0.08959 -0.0427 0.1070 1.0000