XFOIL Version 6.96 Calculated polar for: FX 73-K-170/22 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.0698 0.10032 0.09449 -0.1295 0.8754 0.0261 -11.750 -0.0690 0.09578 0.08998 -0.1319 0.8723 0.0256 -11.500 -0.0695 0.09086 0.08508 -0.1347 0.8693 0.0252 -11.000 -0.1290 0.06730 0.06141 -0.1497 0.8633 0.0223 -10.750 -0.1423 0.06295 0.05702 -0.1520 0.8591 0.0221 -10.500 -0.1665 0.05803 0.05195 -0.1546 0.8545 0.0221 -10.250 -0.1812 0.05447 0.04824 -0.1558 0.8505 0.0220 -10.000 -0.1919 0.05217 0.04585 -0.1553 0.8460 0.0218 -9.750 -0.2123 0.04962 0.04314 -0.1538 0.8407 0.0218 -9.500 -0.2268 0.04770 0.04105 -0.1517 0.8364 0.0218 -9.250 -0.2371 0.04590 0.03904 -0.1493 0.8322 0.0217 -9.000 -0.2467 0.04408 0.03698 -0.1464 0.8270 0.0218 -8.750 -0.2482 0.04202 0.03460 -0.1443 0.8232 0.0218 -8.500 -0.2424 0.03999 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0.9638 0.04270 0.03506 -0.0771 0.5511 1.0000 8.250 0.9997 0.04190 0.03434 -0.0778 0.5495 1.0000 8.500 1.0009 0.04389 0.03640 -0.0763 0.5369 1.0000 8.750 1.0367 0.04295 0.03556 -0.0768 0.5349 1.0000 9.000 1.0392 0.04483 0.03753 -0.0753 0.5224 1.0000 9.250 1.0758 0.04370 0.03650 -0.0758 0.5200 1.0000 9.500 1.0799 0.04540 0.03829 -0.0744 0.5076 1.0000 9.750 1.1188 0.04393 0.03696 -0.0748 0.5046 1.0000 10.000 1.1240 0.04549 0.03861 -0.0734 0.4917 1.0000 10.250 1.1353 0.04653 0.03975 -0.0723 0.4800 1.0000 10.500 1.1650 0.04575 0.03908 -0.0720 0.4718 1.0000 10.750 1.1889 0.04544 0.03888 -0.0714 0.4598 1.0000 11.000 1.2057 0.04585 0.03937 -0.0705 0.4448 1.0000 11.250 1.2193 0.04656 0.04012 -0.0694 0.4264 1.0000 11.500 1.2323 0.04731 0.04089 -0.0682 0.4046 1.0000 11.750 1.2471 0.04781 0.04131 -0.0670 0.3776 1.0000 12.000 1.2570 0.04886 0.04227 -0.0657 0.3480 1.0000 12.250 1.2614 0.05052 0.04378 -0.0642 0.3156 1.0000 12.500 1.2642 0.05249 0.04564 -0.0628 0.2867 1.0000 12.750 1.2633 0.05492 0.04791 -0.0614 0.2569 1.0000 13.000 1.2612 0.05758 0.05045 -0.0602 0.2295 1.0000 13.250 1.2581 0.06046 0.05321 -0.0591 0.2042 1.0000 13.500 1.2533 0.06365 0.05629 -0.0581 0.1774 1.0000 13.750 1.2490 0.06689 0.05943 -0.0573 0.1535 1.0000 14.000 1.2436 0.07031 0.06274 -0.0566 0.1326 1.0000 14.250 1.2398 0.07367 0.06606 -0.0561 0.1126 1.0000 14.500 1.2355 0.07716 0.06949 -0.0557 0.0963 1.0000 14.750 1.2313 0.08072 0.07300 -0.0554 0.0829 1.0000 15.000 1.2287 0.08413 0.07641 -0.0552 0.0730 1.0000 15.250 1.2256 0.08766 0.07995 -0.0551 0.0656 1.0000 15.500 1.2240 0.09108 0.08341 -0.0551 0.0588 1.0000 15.750 1.2224 0.09451 0.08688 -0.0552 0.0540 1.0000 16.000 1.2220 0.09784 0.09031 -0.0554 0.0493 1.0000 16.250 1.2186 0.10157 0.09401 -0.0558 0.0458 1.0000