XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0518 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2036 0.08927 0.08414 -0.0508 1.0000 0.0397 -19.500 -1.2062 0.08544 0.08022 -0.0525 1.0000 0.0401 -19.250 -1.2073 0.08189 0.07659 -0.0540 1.0000 0.0406 -19.000 -1.2079 0.07849 0.07310 -0.0553 1.0000 0.0411 -18.750 -1.2073 0.07525 0.06977 -0.0566 1.0000 0.0415 -18.500 -1.2047 0.07234 0.06676 -0.0576 1.0000 0.0420 -18.250 -1.2029 0.06936 0.06371 -0.0586 1.0000 0.0424 -18.000 -1.2019 0.06633 0.06064 -0.0596 1.0000 0.0429 -17.750 -1.1986 0.06363 0.05789 -0.0605 1.0000 0.0433 -17.500 -1.1944 0.06106 0.05527 -0.0612 1.0000 0.0438 -17.250 -1.1886 0.05876 0.05291 -0.0618 1.0000 0.0444 -17.000 -1.1823 0.05652 0.05062 -0.0624 1.0000 0.0450 -16.750 -1.1744 0.05453 0.04857 -0.0628 1.0000 0.0456 -16.500 -1.1665 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0.1789 0.6202 2.750 0.7001 0.01331 0.00547 -0.1021 0.1644 0.6216 3.000 0.7276 0.01358 0.00567 -0.1020 0.1513 0.6231 3.250 0.7550 0.01385 0.00587 -0.1018 0.1397 0.6246 3.500 0.7823 0.01412 0.00607 -0.1017 0.1292 0.6262 3.750 0.8096 0.01439 0.00629 -0.1015 0.1214 0.6277 4.000 0.8369 0.01465 0.00650 -0.1013 0.1149 0.6292 4.250 0.8637 0.01493 0.00674 -0.1011 0.1087 0.6307 4.500 0.8908 0.01519 0.00697 -0.1009 0.1040 0.6320 4.750 0.9170 0.01549 0.00723 -0.1006 0.0995 0.6335 5.000 0.9435 0.01573 0.00749 -0.1002 0.0958 0.6351 5.250 0.9695 0.01601 0.00777 -0.0998 0.0918 0.6368 5.500 0.9950 0.01631 0.00806 -0.0993 0.0885 0.6387 5.750 1.0207 0.01659 0.00836 -0.0988 0.0856 0.6407 6.000 1.0458 0.01691 0.00867 -0.0983 0.0829 0.6427 6.250 1.0704 0.01725 0.00899 -0.0976 0.0805 0.6447 6.500 1.0952 0.01756 0.00932 -0.0970 0.0783 0.6466 6.750 1.1193 0.01790 0.00966 -0.0963 0.0760 0.6485 7.000 1.1425 0.01829 0.01003 -0.0955 0.0741 0.6504 7.250 1.1657 0.01866 0.01040 -0.0946 0.0725 0.6521 7.500 1.1886 0.01901 0.01078 -0.0937 0.0708 0.6537 7.750 1.2105 0.01938 0.01118 -0.0926 0.0690 0.6558 8.000 1.2309 0.01981 0.01162 -0.0913 0.0674 0.6579 8.250 1.2496 0.02024 0.01208 -0.0897 0.0660 0.6599 8.500 1.2671 0.02063 0.01252 -0.0878 0.0647 0.6621 8.750 1.2856 0.02108 0.01301 -0.0862 0.0633 0.6644 9.000 1.3047 0.02157 0.01353 -0.0847 0.0620 0.6667 9.250 1.3232 0.02213 0.01410 -0.0833 0.0607 0.6691 9.500 1.3414 0.02271 0.01471 -0.0818 0.0595 0.6716 9.750 1.3604 0.02325 0.01529 -0.0805 0.0583 0.6741 10.000 1.3787 0.02384 0.01591 -0.0792 0.0570 0.6766 10.250 1.3963 0.02446 0.01659 -0.0777 0.0558 0.6794 10.500 1.4130 0.02516 0.01732 -0.0763 0.0547 0.6822 10.750 1.4288 0.02593 0.01812 -0.0747 0.0538 0.6850 11.000 1.4455 0.02664 0.01890 -0.0734 0.0528 0.6879 11.250 1.4616 0.02742 0.01973 -0.0720 0.0519 0.6909 11.500 1.4772 0.02824 0.02060 -0.0706 0.0509 0.6938 11.750 1.4920 0.02914 0.02153 -0.0692 0.0501 0.6965 12.000 1.5059 0.03011 0.02254 -0.0678 0.0492 0.6992 12.250 1.5184 0.03120 0.02367 -0.0663 0.0484 0.7022 12.500 1.5324 0.03219 0.02476 -0.0650 0.0477 0.7053 12.750 1.5458 0.03325 0.02589 -0.0637 0.0469 0.7086 13.000 1.5582 0.03440 0.02711 -0.0624 0.0461 0.7121 13.250 1.5701 0.03563 0.02840 -0.0612 0.0453 0.7156 13.500 1.5810 0.03697 0.02978 -0.0599 0.0447 0.7190 13.750 1.5906 0.03842 0.03129 -0.0587 0.0441 0.7222 14.000 1.5986 0.04004 0.03297 -0.0575 0.0435 0.7255 14.250 1.6070 0.04165 0.03467 -0.0563 0.0431 0.7289 14.500 1.6157 0.04329 0.03641 -0.0553 0.0426 0.7324 14.750 1.6236 0.04502 0.03823 -0.0543 0.0421 0.7359 15.000 1.6305 0.04688 0.04017 -0.0534 0.0416 0.7392 15.250 1.6366 0.04888 0.04225 -0.0527 0.0411 0.7422 15.500 1.6420 0.05100 0.04446 -0.0519 0.0406 0.7453 15.750 1.6465 0.05327 0.04682 -0.0513 0.0402 0.7485 16.000 1.6495 0.05575 0.04939 -0.0509 0.0398 0.7519 16.250 1.6514 0.05844 0.05216 -0.0505 0.0394 0.7553 16.500 1.6514 0.06142 0.05521 -0.0504 0.0390 0.7585 16.750 1.6496 0.06473 0.05859 -0.0504 0.0386 0.7615 17.000 1.6504 0.06778 0.06176 -0.0506 0.0383 0.7643 17.250 1.6497 0.07105 0.06516 -0.0508 0.0380 0.7671 17.500 1.6480 0.07454 0.06878 -0.0513 0.0376 0.7700 17.750 1.6447 0.07834 0.07271 -0.0520 0.0373 0.7731 18.000 1.6402 0.08241 0.07690 -0.0529 0.0370 0.7762 18.250 1.6341 0.08679 0.08139 -0.0541 0.0367 0.7792 18.500 1.6270 0.09142 0.08614 -0.0556 0.0364 0.7821 18.750 1.6181 0.09642 0.09127 -0.0574 0.0361 0.7846 19.000 1.6076 0.10174 0.09672 -0.0595 0.0359 0.7870 19.250 1.5964 0.10731 0.10242 -0.0619 0.0356 0.7895