XFOIL Version 6.96 Calculated polar for: FX 73-CL3-152 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 0.1808 0.09133 0.08874 -0.1260 0.8303 0.0262 -10.000 -0.1325 0.03891 0.03604 -0.1553 0.8336 0.0253 -9.750 -0.1609 0.02589 0.02259 -0.1746 0.8253 0.0254 -9.500 -0.1389 0.02000 0.01628 -0.1854 0.8174 0.0257 -9.250 -0.1144 0.01854 0.01468 -0.1870 0.8099 0.0260 -9.000 -0.0883 0.01772 0.01380 -0.1878 0.8002 0.0263 -8.750 -0.0620 0.01708 0.01307 -0.1882 0.7891 0.0266 -8.500 -0.0361 0.01647 0.01233 -0.1884 0.7724 0.0270 -8.250 -0.0116 0.01584 0.01150 -0.1883 0.7420 0.0273 -8.000 0.0101 0.01543 0.01078 -0.1876 0.6941 0.0277 -7.750 0.0328 0.01503 0.01011 -0.1870 0.6564 0.0280 -7.500 0.0568 0.01467 0.00952 -0.1865 0.6274 0.0283 -7.250 0.0820 0.01430 0.00897 -0.1862 0.6040 0.0286 -7.000 0.1077 0.01402 0.00851 -0.1859 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1.0000 8.000 1.7065 0.01343 0.00804 -0.1687 0.3494 1.0000 8.250 1.7288 0.01372 0.00833 -0.1679 0.3469 1.0000 8.500 1.7526 0.01389 0.00855 -0.1674 0.3452 1.0000 8.750 1.7759 0.01410 0.00878 -0.1668 0.3431 1.0000 9.000 1.7986 0.01434 0.00905 -0.1662 0.3408 1.0000 9.250 1.8203 0.01462 0.00934 -0.1654 0.3384 1.0000 9.500 1.8408 0.01496 0.00968 -0.1644 0.3358 1.0000 9.750 1.8596 0.01540 0.01010 -0.1633 0.3326 1.0000 10.000 1.8805 0.01574 0.01047 -0.1624 0.3304 1.0000 10.250 1.9023 0.01601 0.01080 -0.1618 0.3284 1.0000 10.500 1.9235 0.01632 0.01115 -0.1610 0.3258 1.0000 10.750 1.9431 0.01672 0.01156 -0.1600 0.3226 1.0000 11.000 1.9603 0.01723 0.01206 -0.1588 0.3189 1.0000 11.250 1.9776 0.01775 0.01259 -0.1576 0.3147 1.0000 11.500 1.9981 0.01811 0.01299 -0.1569 0.3107 1.0000 11.750 2.0155 0.01863 0.01353 -0.1558 0.3064 1.0000 12.000 2.0298 0.01934 0.01423 -0.1543 0.3019 1.0000 12.250 2.0470 0.01989 0.01482 -0.1532 0.2987 1.0000 12.500 2.0650 0.02041 0.01538 -0.1522 0.2952 1.0000 12.750 2.0804 0.02107 0.01607 -0.1510 0.2918 1.0000 13.000 2.0930 0.02192 0.01692 -0.1494 0.2880 1.0000 13.250 2.1065 0.02273 0.01776 -0.1480 0.2845 1.0000 13.500 2.1222 0.02339 0.01849 -0.1469 0.2819 1.0000 13.750 2.1359 0.02420 0.01933 -0.1456 0.2781 1.0000 14.000 2.1451 0.02532 0.02046 -0.1439 0.2735 1.0000 14.250 2.1549 0.02642 0.02158 -0.1424 0.2692 1.0000 14.500 2.1674 0.02734 0.02255 -0.1411 0.2648 1.0000 14.750 2.1747 0.02866 0.02389 -0.1394 0.2604 1.0000 15.000 2.1783 0.03029 0.02554 -0.1375 0.2557 1.0000 15.250 2.1903 0.03133 0.02666 -0.1364 0.2526 1.0000 15.500 2.1969 0.03282 0.02818 -0.1349 0.2480 1.0000 15.750 2.1967 0.03494 0.03032 -0.1331 0.2427 1.0000 16.000 2.2029 0.03659 0.03203 -0.1318 0.2384 1.0000 16.250 2.2044 0.03871 0.03419 -0.1304 0.2326 1.0000 16.500 2.1980 0.04166 0.03716 -0.1287 0.2268 1.0000 16.750 2.1998 0.04392 0.03948 -0.1276 0.2208 1.0000 17.000 2.1892 0.04753 0.04312 -0.1262 0.2141 1.0000 17.250 2.1834 0.05072 0.04637 -0.1251 0.2074 1.0000 17.500 2.1652 0.05540 0.05108 -0.1239 0.2003 1.0000 17.750 2.1499 0.05987 0.05560 -0.1230 0.1926 1.0000 18.000 2.1206 0.06606 0.06183 -0.1221 0.1845 1.0000 18.250 2.0919 0.07232 0.06814 -0.1215 0.1758 1.0000 18.500 2.0595 0.07917 0.07505 -0.1211 0.1682 1.0000 18.750 2.0224 0.08674 0.08267 -0.1209 0.1606 1.0000