XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0714 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.8006 0.07178 0.06477 -0.0703 1.0000 0.0509 -13.500 -0.8352 0.06590 0.05866 -0.0714 1.0000 0.0510 -13.250 -0.8598 0.06173 0.05431 -0.0709 1.0000 0.0511 -13.000 -0.8803 0.05839 0.05080 -0.0696 1.0000 0.0514 -12.750 -0.8984 0.05561 0.04786 -0.0675 1.0000 0.0517 -12.500 -0.9159 0.05328 0.04539 -0.0646 1.0000 0.0521 -12.250 -0.9337 0.05129 0.04326 -0.0610 1.0000 0.0525 -12.000 -0.9457 0.04916 0.04095 -0.0583 1.0000 0.0532 -11.750 -0.9520 0.04682 0.03836 -0.0564 1.0000 0.0540 -11.500 -0.9544 0.04437 0.03555 -0.0552 1.0000 0.0551 -11.250 -0.9446 0.04290 0.03404 -0.0540 1.0000 0.0560 -11.000 -0.9331 0.04163 0.03272 -0.0530 1.0000 0.0569 -10.750 -0.9209 0.04027 0.03128 -0.0520 1.0000 0.0580 -10.500 -0.9076 0.03883 0.02969 -0.0510 1.0000 0.0592 -10.250 -0.8931 0.03736 0.02803 -0.0501 1.0000 0.0607 -10.000 -0.8774 0.03594 0.02631 -0.0493 1.0000 0.0625 -9.750 -0.8601 0.03491 0.02533 -0.0485 1.0000 0.0640 -9.500 -0.8420 0.03399 0.02441 -0.0478 1.0000 0.0657 -9.250 -0.8232 0.03302 0.02336 -0.0471 1.0000 0.0676 -9.000 -0.8038 0.03203 0.02222 -0.0464 1.0000 0.0697 -8.750 -0.7840 0.03112 0.02124 -0.0456 1.0000 0.0718 -8.500 -0.7638 0.03035 0.02054 -0.0451 1.0000 0.0740 -8.250 -0.7427 0.02963 0.01978 -0.0447 1.0000 0.0768 -8.000 -0.7211 0.02892 0.01897 -0.0441 1.0000 0.0798 -7.750 -0.6996 0.02820 0.01830 -0.0437 1.0000 0.0825 -7.500 -0.6771 0.02757 0.01770 -0.0435 1.0000 0.0861 -7.250 -0.6540 0.02700 0.01706 -0.0432 1.0000 0.0902 -7.000 -0.6307 0.02634 0.01647 -0.0432 1.0000 0.0941 -6.750 -0.6063 0.02579 0.01595 -0.0434 1.0000 0.0993 -6.500 -0.5794 0.02524 0.01542 -0.0440 0.9994 0.1051 -6.250 -0.5471 0.02471 0.01495 -0.0457 0.9976 0.1126 -6.000 -0.5140 0.02420 0.01452 -0.0476 0.9958 0.1220 -5.750 -0.4804 0.02376 0.01414 -0.0495 0.9941 0.1346 -5.500 -0.4459 0.02330 0.01381 -0.0518 0.9928 0.1519 -5.250 -0.4121 0.02280 0.01347 -0.0539 0.9908 0.1787 -5.000 -0.3749 0.02209 0.01309 -0.0572 0.9892 0.2277 -4.750 -0.3290 0.02084 0.01267 -0.0633 0.9890 0.3584 -4.500 -0.3093 0.02132 0.01402 -0.0603 0.9857 0.4767 -4.250 -0.2897 0.02248 0.01539 -0.0567 0.9819 0.5356 -4.000 -0.2542 0.02280 0.01562 -0.0586 0.9792 0.5727 -3.750 -0.2158 0.02297 0.01565 -0.0615 0.9763 0.6004 -3.500 -0.1836 0.02349 0.01609 -0.0622 0.9727 0.6178 -3.250 -0.1579 0.02429 0.01688 -0.0607 0.9692 0.6275 -2.750 -0.1044 0.02542 0.01795 -0.0595 0.9609 0.6539 -2.500 -0.0870 0.02639 0.01897 -0.0555 0.9562 0.6633 -2.250 -0.0587 0.02701 0.01958 -0.0547 0.9527 0.6753 -2.000 -0.0389 0.02730 0.01988 -0.0526 0.9462 0.6820 -1.750 0.0036 0.02716 0.01967 -0.0568 0.9430 0.6902 -1.500 0.0332 0.02728 0.01979 -0.0568 0.9394 0.6928 -1.250 0.0584 0.02734 0.01986 -0.0561 0.9337 0.6959 -1.000 0.0885 0.02731 0.01985 -0.0567 0.9279 0.6994 -0.750 0.1280 0.02720 0.01973 -0.0593 0.9238 0.7036 -0.500 0.1687 0.02698 0.01950 -0.0628 0.9176 0.7084 -0.250 0.2027 0.02677 0.01932 -0.0640 0.9099 0.7110 0.250 0.2645 0.02644 0.01910 -0.0647 0.8947 0.7154 0.500 0.3108 0.02589 0.01861 -0.0676 0.8881 0.7178 0.750 0.3486 0.02517 0.01793 -0.0687 0.8725 0.7206 1.000 0.3901 0.02424 0.01706 -0.0703 0.8550 0.7238 1.250 0.4325 0.02335 0.01621 -0.0724 0.8365 0.7271 1.500 0.4607 0.02290 0.01582 -0.0723 0.8118 0.7293 1.750 0.4923 0.02231 0.01530 -0.0720 0.7856 0.7306 2.000 0.5245 0.02177 0.01476 -0.0718 0.7445 0.7322 2.250 0.5977 0.02079 0.01324 -0.0782 0.6162 0.7335 2.500 0.6251 0.02160 0.01310 -0.0776 0.4541 0.7352 2.750 0.6438 0.02256 0.01341 -0.0762 0.3394 0.7369 3.000 0.6650 0.02343 0.01376 -0.0755 0.2529 0.7387 3.250 0.6893 0.02414 0.01414 -0.0754 0.1984 0.7405 3.500 0.7153 0.02477 0.01455 -0.0756 0.1669 0.7428 3.750 0.7427 0.02539 0.01502 -0.0761 0.1463 0.7454 4.000 0.7714 0.02598 0.01553 -0.0769 0.1320 0.7476 4.250 0.7939 0.02650 0.01604 -0.0760 0.1225 0.7488 4.500 0.8159 0.02710 0.01658 -0.0752 0.1146 0.7500 4.750 0.8395 0.02762 0.01715 -0.0745 0.1077 0.7514 5.000 0.8624 0.02827 0.01775 -0.0739 0.1022 0.7529 5.250 0.8865 0.02893 0.01844 -0.0734 0.0974 0.7545 5.500 0.9109 0.02959 0.01911 -0.0730 0.0926 0.7565 5.750 0.9353 0.03041 0.01987 -0.0728 0.0887 0.7586 6.000 0.9625 0.03113 0.02071 -0.0730 0.0846 0.7608 6.250 0.9893 0.03190 0.02147 -0.0733 0.0808 0.7628 6.500 1.0173 0.03284 0.02239 -0.0740 0.0778 0.7646 6.750 1.0430 0.03367 0.02336 -0.0738 0.0745 0.7661 7.000 1.0657 0.03446 0.02419 -0.0732 0.0718 0.7674 7.250 1.0891 0.03543 0.02511 -0.0728 0.0697 0.7688 7.500 1.1136 0.03653 0.02642 -0.0723 0.0672 0.7704 7.750 1.1366 0.03758 0.02762 -0.0718 0.0648 0.7723 8.000 1.1588 0.03856 0.02865 -0.0713 0.0628 0.7744 8.250 1.1823 0.03975 0.02981 -0.0711 0.0611 0.7767 8.500 1.2051 0.04133 0.03172 -0.0706 0.0592 0.7789 8.750 1.2271 0.04293 0.03355 -0.0703 0.0575 0.7809 9.000 1.2478 0.04435 0.03512 -0.0698 0.0559 0.7828 9.250 1.2645 0.04554 0.03638 -0.0685 0.0548 0.7842 9.500 1.2802 0.04701 0.03795 -0.0672 0.0536 0.7857 9.750 1.2881 0.04918 0.04056 -0.0647 0.0522 0.7873 10.000 1.2954 0.05128 0.04299 -0.0623 0.0510 0.7891 10.250 1.2999 0.05335 0.04533 -0.0597 0.0502 0.7910 10.500 1.3013 0.05541 0.04763 -0.0568 0.0495 0.7932 10.750 1.3038 0.05762 0.05004 -0.0544 0.0489 0.7955 11.000 1.3064 0.05986 0.05246 -0.0524 0.0484 0.7978 11.250 1.3093 0.06207 0.05480 -0.0506 0.0479 0.7999 11.500 1.3094 0.06433 0.05717 -0.0485 0.0474 0.8015 11.750 1.2860 0.06863 0.06192 -0.0454 0.0471 0.8027 12.000 1.2585 0.07364 0.06735 -0.0432 0.0468 0.8039 12.250 1.2280 0.07948 0.07358 -0.0425 0.0466 0.8049 12.500 1.1926 0.08668 0.08113 -0.0438 0.0466 0.8058 12.750 1.1511 0.09603 0.09083 -0.0480 0.0467 0.8064 13.000 1.0968 0.11022 0.10536 -0.0577 0.0470 0.8065