XFOIL Version 6.96 Calculated polar for: FX 79-W-151 A 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 -0.3846 0.09667 0.09189 -0.0573 1.0000 0.0358 -11.750 -0.4446 0.08035 0.07571 -0.0654 1.0000 0.0361 -11.500 -0.4966 0.06696 0.06235 -0.0737 1.0000 0.0350 -11.250 -0.5463 0.05728 0.05263 -0.0804 1.0000 0.0333 -11.000 -0.5796 0.04955 0.04457 -0.0877 0.9807 0.0331 -10.750 -0.5901 0.04441 0.03898 -0.0912 0.9626 0.0339 -10.500 -0.5920 0.04063 0.03473 -0.0920 0.9477 0.0349 -10.250 -0.5891 0.03762 0.03125 -0.0916 0.9346 0.0367 -10.000 -0.5723 0.03665 0.03028 -0.0914 0.9240 0.0387 -9.750 -0.5585 0.03514 0.02855 -0.0907 0.9142 0.0408 -9.500 -0.5495 0.03330 0.02635 -0.0890 0.9030 0.0433 -9.250 -0.5384 0.03172 0.02446 -0.0872 0.8927 0.0461 -9.000 -0.5207 0.03101 0.02370 -0.0862 0.8847 0.0491 -8.750 -0.5066 0.02995 0.02240 -0.0844 0.8746 0.0525 -8.500 -0.4900 0.02869 0.02082 -0.0829 0.8665 0.0564 -8.250 -0.4719 0.02815 0.02026 -0.0817 0.8578 0.0603 -8.000 -0.4532 0.02725 0.01910 -0.0803 0.8498 0.0651 -7.750 -0.4340 0.02653 0.01826 -0.0791 0.8420 0.0698 -7.500 -0.4142 0.02591 0.01752 -0.0779 0.8343 0.0749 -7.250 -0.3934 0.02513 0.01648 -0.0767 0.8268 0.0808 -7.000 -0.3728 0.02468 0.01598 -0.0756 0.8194 0.0866 -6.750 -0.3509 0.02403 0.01509 -0.0746 0.8121 0.0935 -6.500 -0.3293 0.02359 0.01462 -0.0736 0.8052 0.0999 -6.250 -0.3070 0.02308 0.01390 -0.0726 0.7976 0.1076 -6.000 -0.2841 0.02261 0.01338 -0.0717 0.7916 0.1146 -5.750 -0.2618 0.02220 0.01281 -0.0708 0.7836 0.1227 -5.500 -0.2378 0.02173 0.01229 -0.0700 0.7781 0.1302 -5.250 -0.2154 0.02137 0.01182 -0.0691 0.7701 0.1383 -5.000 -0.1914 0.02097 0.01134 -0.0684 0.7642 0.1468 -4.750 -0.1684 0.02061 0.01093 -0.0676 0.7572 0.1553 -4.500 -0.1443 0.02026 0.01049 -0.0669 0.7507 0.1645 -4.250 -0.1205 0.01988 0.01008 -0.0661 0.7447 0.1730 -4.000 -0.0973 0.01959 0.00974 -0.0653 0.7375 0.1837 -3.750 -0.0724 0.01923 0.00932 -0.0646 0.7324 0.1952 -3.500 -0.0504 0.01897 0.00910 -0.0637 0.7248 0.2075 -3.250 -0.0262 0.01864 0.00877 -0.0629 0.7190 0.2238 -3.000 -0.0030 0.01839 0.00852 -0.0621 0.7127 0.2439 -2.750 0.0199 0.01809 0.00830 -0.0612 0.7061 0.2685 -2.500 0.0445 0.01771 0.00800 -0.0605 0.7013 0.3061 -2.250 0.0652 0.01744 0.00793 -0.0594 0.6938 0.3566 -2.000 0.0882 0.01701 0.00775 -0.0584 0.6883 0.4305 -1.750 0.1101 0.01664 0.00771 -0.0572 0.6820 0.5212 -1.500 0.1350 0.01628 0.00770 -0.0564 0.6758 0.6241 -1.250 0.1724 0.01595 0.00765 -0.0575 0.6712 0.7342 -1.000 0.2239 0.01599 0.00785 -0.0618 0.6638 0.8201 -0.750 0.2763 0.01607 0.00785 -0.0661 0.6583 0.8722 -0.500 0.3229 0.01623 0.00791 -0.0695 0.6520 0.9073 -0.250 0.3650 0.01643 0.00799 -0.0720 0.6455 0.9359 0.000 0.4153 0.01654 0.00793 -0.0762 0.6404 0.9576 0.250 0.4628 0.01671 0.00803 -0.0804 0.6328 0.9780 0.500 0.5190 0.01667 0.00783 -0.0863 0.6272 0.9936 0.750 0.5542 0.01674 0.00784 -0.0883 0.6207 1.0000 1.000 0.5743 0.01680 0.00782 -0.0872 0.6146 1.0000 1.250 0.5956 0.01684 0.00776 -0.0862 0.6096 1.0000 1.500 0.6144 0.01702 0.00793 -0.0849 0.6027 1.0000 1.750 0.6359 0.01710 0.00793 -0.0839 0.5975 1.0000 2.000 0.6561 0.01726 0.00805 -0.0827 0.5917 1.0000 2.250 0.6762 0.01744 0.00821 -0.0815 0.5855 1.0000 2.500 0.6989 0.01753 0.00821 -0.0806 0.5808 1.0000 2.750 0.7178 0.01779 0.00849 -0.0793 0.5744 1.0000 3.000 0.7390 0.01796 0.00863 -0.0782 0.5688 1.0000 3.250 0.7619 0.01810 0.00872 -0.0774 0.5643 1.0000 3.500 0.7801 0.01842 0.00909 -0.0759 0.5579 1.0000 3.750 0.8020 0.01861 0.00925 -0.0749 0.5528 1.0000 4.000 0.8237 0.01883 0.00944 -0.0739 0.5478 1.0000 4.250 0.8423 0.01915 0.00983 -0.0725 0.5415 1.0000 4.500 0.8648 0.01935 0.01001 -0.0716 0.5369 1.0000 4.750 0.8854 0.01964 0.01032 -0.0705 0.5319 1.0000 5.000 0.9039 0.02000 0.01075 -0.0691 0.5261 1.0000 5.250 0.9269 0.02020 0.01094 -0.0682 0.5214 1.0000 5.500 0.9460 0.02056 0.01136 -0.0669 0.5161 1.0000 5.750 0.9644 0.02095 0.01182 -0.0655 0.5107 1.0000 6.000 0.9875 0.02118 0.01208 -0.0647 0.5064 1.0000 6.250 1.0061 0.02158 0.01255 -0.0633 0.5012 1.0000 6.500 1.0234 0.02202 0.01308 -0.0618 0.4957 1.0000 6.750 1.0465 0.02227 0.01336 -0.0610 0.4914 1.0000 7.000 1.0654 0.02271 0.01390 -0.0597 0.4869 1.0000 7.250 1.0804 0.02325 0.01456 -0.0579 0.4813 1.0000 7.500 1.1028 0.02354 0.01491 -0.0570 0.4769 1.0000 7.750 1.1222 0.02396 0.01541 -0.0558 0.4723 1.0000 8.000 1.1343 0.02460 0.01619 -0.0536 0.4665 1.0000 8.250 1.1557 0.02495 0.01664 -0.0527 0.4622 1.0000 8.500 1.1765 0.02534 0.01712 -0.0516 0.4578 1.0000 8.750 1.1840 0.02612 0.01808 -0.0488 0.4519 1.0000 9.000 1.2057 0.02640 0.01843 -0.0479 0.4467 1.0000 9.250 1.2185 0.02697 0.01913 -0.0458 0.4410 1.0000 9.500 1.2275 0.02757 0.01989 -0.0431 0.4342 1.0000 9.750 1.2486 0.02775 0.02014 -0.0420 0.4279 1.0000 10.000 1.2447 0.02860 0.02114 -0.0376 0.4201 1.0000 10.250 1.2531 0.02892 0.02151 -0.0347 0.4108 1.0000 10.500 1.2544 0.02929 0.02191 -0.0310 0.3975 1.0000 10.750 1.2485 0.03018 0.02282 -0.0271 0.3823 1.0000 11.000 1.2382 0.03162 0.02430 -0.0234 0.3649 1.0000 11.250 1.2307 0.03330 0.02601 -0.0206 0.3475 1.0000 11.500 1.2226 0.03522 0.02791 -0.0181 0.3265 1.0000 11.750 1.2142 0.03764 0.03039 -0.0161 0.3078 1.0000 12.000 1.2061 0.04028 0.03304 -0.0145 0.2867 1.0000 12.250 1.1987 0.04302 0.03576 -0.0132 0.2632 1.0000 12.500 1.1894 0.04603 0.03868 -0.0120 0.2361 1.0000 12.750 1.1732 0.04988 0.04232 -0.0109 0.2023 1.0000 13.000 1.1550 0.05425 0.04648 -0.0102 0.1732 1.0000 13.250 1.1408 0.05848 0.05061 -0.0099 0.1522 1.0000 13.500 1.1234 0.06328 0.05528 -0.0098 0.1282 1.0000 13.750 1.1066 0.06821 0.06009 -0.0100 0.1050 1.0000 14.000 1.0912 0.07314 0.06491 -0.0103 0.0853 1.0000 14.250 1.0805 0.07759 0.06932 -0.0107 0.0715 1.0000 14.500 1.0690 0.08227 0.07392 -0.0113 0.0584 1.0000 14.750 1.0598 0.08674 0.07838 -0.0118 0.0497 1.0000 15.000 1.0510 0.09124 0.08284 -0.0125 0.0434 1.0000 15.250 1.0473 0.09509 0.08678 -0.0130 0.0394 1.0000