XFOIL Version 6.96 Calculated polar for: FX S 03-182 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.4842 0.10495 0.10246 -0.0706 0.9815 0.0030 -15.000 -0.5284 0.08780 0.08507 -0.0804 0.9713 0.0029 -14.750 -0.5465 0.07620 0.07323 -0.0903 0.9582 0.0029 -14.500 -0.5506 0.06705 0.06382 -0.1003 0.9466 0.0028 -14.250 -0.5480 0.05887 0.05533 -0.1107 0.9356 0.0028 -14.000 -0.5395 0.05195 0.04807 -0.1205 0.9210 0.0028 -13.750 -0.5297 0.04665 0.04240 -0.1278 0.9006 0.0028 -13.500 -0.5246 0.04337 0.03882 -0.1306 0.8767 0.0028 -13.250 -0.5242 0.04086 0.03606 -0.1311 0.8563 0.0028 -13.000 -0.5235 0.03876 0.03373 -0.1309 0.8402 0.0028 -12.750 -0.5234 0.03668 0.03143 -0.1302 0.8266 0.0028 -12.500 -0.5207 0.03490 0.02946 -0.1295 0.8144 0.0028 -12.250 -0.5183 0.03306 0.02741 -0.1284 0.8039 0.0029 -12.000 -0.5100 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8.000 0.9832 0.02566 0.01715 -0.0635 0.0093 0.6763 8.250 0.9988 0.02648 0.01800 -0.0627 0.0090 0.6787 8.500 1.0143 0.02732 0.01888 -0.0620 0.0081 0.6812 8.750 1.0294 0.02819 0.01982 -0.0612 0.0072 0.6835 9.000 1.0412 0.02930 0.02097 -0.0602 0.0028 0.6859 9.250 1.0542 0.03036 0.02208 -0.0593 0.0026 0.6887 9.500 1.0666 0.03148 0.02326 -0.0584 0.0023 0.6916 9.750 1.0801 0.03255 0.02438 -0.0576 0.0023 0.6946 10.000 1.0933 0.03366 0.02554 -0.0568 0.0022 0.6975 10.250 1.1061 0.03481 0.02677 -0.0561 0.0022 0.7006 10.500 1.1187 0.03601 0.02806 -0.0554 0.0021 0.7041 10.750 1.1312 0.03724 0.02936 -0.0547 0.0021 0.7080 11.250 1.1551 0.03986 0.03213 -0.0533 0.0020 0.7155 11.500 1.1668 0.04122 0.03358 -0.0527 0.0020 0.7197 11.750 1.1780 0.04266 0.03510 -0.0521 0.0019 0.7239 12.000 1.1890 0.04416 0.03668 -0.0516 0.0019 0.7281 12.250 1.1994 0.04572 0.03833 -0.0510 0.0018 0.7326 12.500 1.2092 0.04737 0.04009 -0.0505 0.0017 0.7376 12.750 1.2188 0.04907 0.04189 -0.0500 0.0017 0.7424 13.000 1.2277 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0.10540 -0.0537 0.0012 1.0000 18.000 1.2465 0.11555 0.11115 -0.0559 0.0012 1.0000