XFOIL Version 6.96 Calculated polar for: FX 73-CL2-152 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.5588 0.05255 0.05003 -0.1071 0.9819 0.0262 -12.000 -0.5724 0.04382 0.04111 -0.1192 0.9767 0.0264 -11.750 -0.5858 0.03727 0.03441 -0.1266 0.9688 0.0265 -11.500 -0.5590 0.03082 0.02777 -0.1402 0.9659 0.0268 -11.250 -0.5310 0.02621 0.02297 -0.1507 0.9610 0.0271 -11.000 -0.4935 0.02335 0.01993 -0.1588 0.9577 0.0275 -10.750 -0.4554 0.02170 0.01814 -0.1637 0.9559 0.0279 -10.500 -0.4164 0.02045 0.01678 -0.1677 0.9544 0.0281 -10.250 -0.3762 0.01839 0.01457 -0.1731 0.9532 0.0288 -10.000 -0.3534 0.01759 0.01375 -0.1730 0.9467 0.0292 -9.750 -0.3188 0.01686 0.01300 -0.1749 0.9431 0.0297 -9.500 -0.2816 0.01608 0.01217 -0.1773 0.9401 0.0302 -9.250 -0.2577 0.01547 0.01151 -0.1769 0.9297 0.0306 -9.000 -0.2209 0.01471 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1.0000 10.750 2.0268 0.01639 0.01108 -0.1856 0.2752 1.0000 11.000 2.0453 0.01682 0.01151 -0.1841 0.2707 1.0000 11.250 2.0615 0.01735 0.01204 -0.1822 0.2658 1.0000 11.500 2.0813 0.01771 0.01245 -0.1810 0.2626 1.0000 11.750 2.0994 0.01816 0.01292 -0.1795 0.2583 1.0000 12.000 2.1144 0.01876 0.01352 -0.1775 0.2533 1.0000 12.250 2.1303 0.01932 0.01411 -0.1757 0.2485 1.0000 12.500 2.1470 0.01984 0.01467 -0.1741 0.2438 1.0000 12.750 2.1598 0.02057 0.01540 -0.1719 0.2382 1.0000 13.000 2.1736 0.02127 0.01612 -0.1699 0.2331 1.0000 13.250 2.1868 0.02200 0.01688 -0.1679 0.2271 1.0000 13.500 2.1951 0.02304 0.01791 -0.1654 0.2198 1.0000 13.750 2.2062 0.02393 0.01883 -0.1632 0.2122 1.0000 14.000 2.2112 0.02522 0.02011 -0.1604 0.2030 1.0000 14.250 2.2120 0.02686 0.02171 -0.1573 0.1915 1.0000 14.500 2.2088 0.02885 0.02367 -0.1540 0.1784 1.0000 15.000 2.1865 0.03450 0.02926 -0.1471 0.1518 1.0000 15.250 2.1720 0.03801 0.03278 -0.1442 0.1410 1.0000 15.500 2.1574 0.04187 0.03668 -0.1420 0.1326 1.0000 15.750 2.1384 0.04662 0.04148 -0.1404 0.1253 1.0000 16.000 2.1228 0.05140 0.04633 -0.1395 0.1192 1.0000 16.500 2.0819 0.06330 0.05842 -0.1396 0.1096 1.0000 16.750 2.0569 0.07034 0.06556 -0.1403 0.1056 1.0000 17.000 2.0310 0.07776 0.07309 -0.1415 0.1019 1.0000 17.250 2.0104 0.08455 0.08000 -0.1427 0.0988 1.0000