XFOIL Version 6.96 Calculated polar for: NACA 64(4)-421 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.6929 0.09816 0.09162 -0.0713 1.0000 0.0504 -17.000 -0.7268 0.08941 0.08261 -0.0759 1.0000 0.0505 -16.750 -0.7468 0.08332 0.07630 -0.0788 1.0000 0.0509 -16.500 -0.7616 0.07826 0.07104 -0.0810 1.0000 0.0513 -16.250 -0.7719 0.07393 0.06652 -0.0825 1.0000 0.0518 -16.000 -0.7795 0.07010 0.06249 -0.0837 1.0000 0.0524 -15.750 -0.7855 0.06658 0.05877 -0.0846 1.0000 0.0531 -15.500 -0.7899 0.06336 0.05531 -0.0852 1.0000 0.0538 -15.250 -0.7816 0.06149 0.05343 -0.0853 1.0000 0.0546 -15.000 -0.7732 0.05981 0.05175 -0.0853 1.0000 0.0557 -14.750 -0.7660 0.05796 0.04985 -0.0853 1.0000 0.0566 -14.500 -0.7597 0.05610 0.04791 -0.0852 1.0000 0.0578 -14.250 -0.7527 0.05430 0.04599 -0.0849 1.0000 0.0591 -14.000 -0.7450 0.05260 0.04414 -0.0845 1.0000 0.0603 -13.750 -0.7323 0.05148 0.04308 -0.0839 1.0000 0.0616 -13.500 -0.7218 0.05032 0.04196 -0.0833 1.0000 0.0628 -13.250 -0.7133 0.04916 0.04079 -0.0824 1.0000 0.0644 -13.000 -0.7063 0.04808 0.03968 -0.0813 1.0000 0.0662 -12.750 -0.6986 0.04711 0.03866 -0.0801 0.9976 0.0680 -12.500 -0.6696 0.04569 0.03731 -0.0826 0.9795 0.0704 -12.250 -0.6417 0.04439 0.03596 -0.0850 0.9658 0.0735 -12.000 -0.6133 0.04311 0.03462 -0.0874 0.9536 0.0771 -11.750 -0.5865 0.04180 0.03330 -0.0898 0.9411 0.0810 -11.500 -0.5597 0.04064 0.03208 -0.0917 0.9288 0.0857 -11.250 -0.5366 0.03938 0.03080 -0.0935 0.9165 0.0906 -11.000 -0.5162 0.03826 0.02964 -0.0944 0.9034 0.0965 -10.750 -0.5007 0.03717 0.02853 -0.0945 0.8901 0.1028 -10.500 -0.4871 0.03607 0.02741 -0.0944 0.8783 0.1099 -10.250 -0.4750 0.03504 0.02634 -0.0938 0.8665 0.1187 -10.000 -0.4662 0.03391 0.02524 -0.0929 0.8553 0.1282 -9.750 -0.4586 0.03272 0.02407 -0.0919 0.8450 0.1398 -9.500 -0.4534 0.03150 0.02289 -0.0907 0.8346 0.1533 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0.5564 -4.500 -0.1943 0.02466 0.01611 -0.0592 0.6985 0.5649 -4.250 -0.1713 0.02460 0.01599 -0.0587 0.6930 0.5698 -4.000 -0.1440 0.02471 0.01603 -0.0583 0.6885 0.5728 -3.750 -0.1173 0.02463 0.01586 -0.0582 0.6848 0.5764 -3.500 -0.0925 0.02435 0.01544 -0.0582 0.6813 0.5811 -3.250 -0.0747 0.02380 0.01477 -0.0580 0.6756 0.5874 -3.000 -0.0488 0.02384 0.01478 -0.0577 0.6709 0.5896 -2.750 -0.0218 0.02380 0.01468 -0.0575 0.6670 0.5920 -2.500 0.0059 0.02370 0.01449 -0.0575 0.6639 0.5949 -2.250 0.0304 0.02363 0.01437 -0.0574 0.6600 0.5984 -2.000 0.0526 0.02350 0.01420 -0.0572 0.6554 0.6027 -1.750 0.0768 0.02320 0.01378 -0.0577 0.6515 0.6076 -1.500 0.1036 0.02320 0.01376 -0.0575 0.6483 0.6096 -1.250 0.1314 0.02317 0.01368 -0.0576 0.6456 0.6118 -1.000 0.1600 0.02312 0.01357 -0.0579 0.6434 0.6145 -0.750 0.1811 0.02327 0.01376 -0.0573 0.6391 0.6176 -0.500 0.2044 0.02330 0.01378 -0.0572 0.6350 0.6209 -0.250 0.2301 0.02322 0.01364 -0.0575 0.6315 0.6244 0.000 0.2579 0.02309 0.01344 -0.0581 0.6286 0.6281 0.250 0.2859 0.02312 0.01345 -0.0581 0.6262 0.6304 0.500 0.3148 0.02315 0.01346 -0.0584 0.6243 0.6330 0.750 0.3338 0.02349 0.01388 -0.0575 0.6203 0.6359 1.000 0.3549 0.02375 0.01419 -0.0571 0.6167 0.6391 1.250 0.3790 0.02391 0.01436 -0.0570 0.6136 0.6427 1.500 0.4058 0.02397 0.01439 -0.0575 0.6109 0.6468 1.750 0.4334 0.02402 0.01444 -0.0577 0.6085 0.6497 2.000 0.4620 0.02408 0.01451 -0.0579 0.6065 0.6524 2.250 0.4892 0.02423 0.01470 -0.0581 0.6045 0.6557 2.500 0.4997 0.02498 0.01558 -0.0562 0.5999 0.6598 2.750 0.5182 0.02543 0.01609 -0.0555 0.5960 0.6645 3.000 0.5425 0.02567 0.01635 -0.0555 0.5929 0.6691 3.250 0.5679 0.02585 0.01659 -0.0553 0.5905 0.6722 3.500 0.5963 0.02594 0.01672 -0.0555 0.5884 0.6758 3.750 0.6278 0.02595 0.01675 -0.0562 0.5866 0.6800 4.000 0.6248 0.02722 0.01818 -0.0528 0.5802 0.6850 4.250 0.6380 0.02792 0.01894 -0.0514 0.5757 0.6900 4.500 0.6601 0.02821 0.01933 -0.0508 0.5728 0.6937 4.750 0.6885 0.02830 0.01949 -0.0509 0.5706 0.6983 5.000 0.7209 0.02828 0.01951 -0.0517 0.5688 0.7039 6.000 0.7615 0.03128 0.02289 -0.0440 0.5510 0.7272 6.250 0.8026 0.03092 0.02260 -0.0457 0.5495 0.7330 6.750 0.7704 0.03484 0.02675 -0.0368 0.5330 0.7458 7.000 0.7828 0.03572 0.02771 -0.0356 0.5277 0.7526 7.250 0.8588 0.03289 0.02497 -0.0394 0.5302 0.7585 7.750 0.8490 0.03598 0.02826 -0.0336 0.5133 0.7743 8.250 0.8500 0.03898 0.03146 -0.0296 0.4961 0.7914 8.500 0.8968 0.03704 0.02963 -0.0300 0.4948 0.7997 9.000 0.8420 0.04461 0.03742 -0.0240 0.4646 0.8182 9.250 0.8822 0.04270 0.03561 -0.0237 0.4616 0.8295 9.500 0.9301 0.03998 0.03299 -0.0234 0.4591 0.8409 10.000 0.8914 0.04663 0.03989 -0.0189 0.4285 0.8666 10.500 0.9152 0.04740 0.04091 -0.0161 0.4086 0.9058 10.750 0.9155 0.04936 0.04302 -0.0154 0.3936 0.9421 11.000 0.9252 0.05048 0.04420 -0.0154 0.3791 1.0000 11.250 0.9463 0.05086 0.04461 -0.0156 0.3648 1.0000 11.500 0.9722 0.05063 0.04433 -0.0157 0.3488 1.0000 11.750 0.9990 0.05019 0.04378 -0.0156 0.3285 1.0000 12.000 1.0163 0.05074 0.04419 -0.0153 0.3040 1.0000 12.250 1.0274 0.05196 0.04521 -0.0149 0.2775 1.0000 12.500 1.0325 0.05392 0.04700 -0.0146 0.2527 1.0000 12.750 1.0348 0.05626 0.04918 -0.0144 0.2299 1.0000 13.000 1.0357 0.05884 0.05160 -0.0143 0.2096 1.0000 13.250 1.0371 0.06150 0.05417 -0.0143 0.1914 1.0000 13.500 1.0386 0.06424 0.05682 -0.0145 0.1747 1.0000 13.750 1.0407 0.06696 0.05947 -0.0147 0.1599 1.0000 14.000 1.0429 0.06974 0.06218 -0.0150 0.1469 1.0000 14.500 1.0490 0.07529 0.06766 -0.0158 0.1242 1.0000 14.750 1.0531 0.07799 0.07036 -0.0163 0.1148 1.0000 15.000 1.0566 0.08080 0.07313 -0.0168 0.1066 1.0000 15.250 1.0597 0.08370 0.07601 -0.0174 0.0994 1.0000 15.500 1.0650 0.08637 0.07871 -0.0180 0.0926 1.0000 15.750 1.0681 0.08931 0.08162 -0.0187 0.0871 1.0000 16.000 1.0733 0.09206 0.08443 -0.0194 0.0816 1.0000 16.250 1.0777 0.09488 0.08724 -0.0201 0.0771 1.0000 16.500 1.0828 0.09767 0.09008 -0.0209 0.0728 1.0000 16.750 1.0874 0.10051 0.09291 -0.0218 0.0693 1.0000 17.000 1.0932 0.10324 0.09572 -0.0226 0.0657 1.0000