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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.6533 0.10077 0.09631 -0.0563 1.0000 0.0630 -13.750 -0.6452 0.09927 0.09484 -0.0553 1.0000 0.0634 -13.500 -0.9131 0.06294 0.05746 -0.0711 1.0000 0.0552 -13.250 -0.9388 0.05986 0.05426 -0.0684 1.0000 0.0551 -13.000 -0.9661 0.05744 0.05172 -0.0644 1.0000 0.0551 -12.750 -0.9909 0.05502 0.04916 -0.0606 1.0000 0.0551 -12.500 -1.0085 0.05198 0.04589 -0.0587 1.0000 0.0551 -12.250 -1.0183 0.04879 0.04243 -0.0573 1.0000 0.0553 -12.000 -1.0158 0.04567 0.03917 -0.0561 1.0000 0.0558 -11.750 -1.0069 0.04363 0.03706 -0.0551 1.0000 0.0564 -11.500 -0.9947 0.04208 0.03546 -0.0541 1.0000 0.0571 -11.250 -0.9821 0.04054 0.03385 -0.0532 1.0000 0.0579 -11.000 -0.9689 0.03892 0.03207 -0.0526 1.0000 0.0590 -10.750 -0.9547 0.03708 0.03000 -0.0523 1.0000 0.0603 -10.500 -0.9384 0.03519 0.02779 -0.0522 1.0000 0.0616 -10.250 -0.9194 0.03359 0.02582 -0.0524 1.0000 0.0627 -10.000 -0.9009 0.03171 0.02397 -0.0515 1.0000 0.0639 -9.750 -0.8802 0.03069 0.02294 -0.0510 1.0000 0.0653 -9.500 -0.8586 0.02976 0.02195 -0.0508 1.0000 0.0670 -9.250 -0.8359 0.02884 0.02090 -0.0506 1.0000 0.0691 -9.000 -0.8115 0.02804 0.01985 -0.0509 1.0000 0.0710 -8.750 -0.7911 0.02678 0.01868 -0.0499 1.0000 0.0730 -8.500 -0.7682 0.02608 0.01801 -0.0495 1.0000 0.0751 -8.250 -0.7443 0.02543 0.01731 -0.0494 1.0000 0.0776 -8.000 -0.7190 0.02491 0.01663 -0.0495 1.0000 0.0803 -7.750 -0.6972 0.02401 0.01586 -0.0488 1.0000 0.0832 -7.500 -0.6726 0.02350 0.01538 -0.0487 1.0000 0.0864 -7.250 -0.6471 0.02303 0.01485 -0.0488 1.0000 0.0898 -7.000 -0.6228 0.02234 0.01423 -0.0486 1.0000 0.0936 -6.750 -0.5966 0.02188 0.01383 -0.0490 1.0000 0.0982 -6.500 -0.5694 0.02154 0.01342 -0.0494 1.0000 0.1030 -6.250 -0.5413 0.02087 0.01292 -0.0503 1.0000 0.1095 -6.000 -0.5122 0.02051 0.01256 -0.0512 1.0000 0.1170 -5.750 -0.4805 0.01999 0.01216 -0.0530 1.0000 0.1274 -5.500 -0.4466 0.01947 0.01177 -0.0553 1.0000 0.1421 -5.250 -0.4080 0.01884 0.01135 -0.0588 1.0000 0.1673 -5.000 -0.3495 0.01749 0.01068 -0.0676 1.0000 0.2701 -4.750 -0.2973 0.01674 0.01149 -0.0739 1.0000 0.5416 -4.500 -0.2757 0.01732 0.01209 -0.0725 1.0000 0.5849 -4.250 -0.2559 0.01796 0.01272 -0.0707 1.0000 0.6061 -4.000 -0.2365 0.01862 0.01335 -0.0688 1.0000 0.6213 -3.750 -0.2109 0.01932 0.01401 -0.0681 0.9986 0.6357 -3.500 -0.1873 0.02044 0.01518 -0.0658 0.9943 0.6422 -3.250 -0.1535 0.02113 0.01581 -0.0667 0.9904 0.6540 -3.000 -0.1314 0.02201 0.01674 -0.0643 0.9851 0.6580 -2.750 -0.1025 0.02290 0.01763 -0.0635 0.9818 0.6648 -2.500 -0.0749 0.02337 0.01808 -0.0632 0.9764 0.6736 -2.250 -0.0542 0.02419 0.01894 -0.0602 0.9709 0.6778 -2.000 -0.0133 0.02483 0.01955 -0.0626 0.9681 0.6909 -1.750 -0.0073 0.02550 0.02030 -0.0562 0.9590 0.6951 -1.500 0.0316 0.02619 0.02097 -0.0578 0.9548 0.7100 -1.250 0.0432 0.02644 0.02128 -0.0528 0.9459 0.7137 -1.000 0.0771 0.02649 0.02135 -0.0531 0.9404 0.7183 -0.750 0.1163 0.02640 0.02125 -0.0555 0.9351 0.7235 -0.500 0.1596 0.02619 0.02103 -0.0598 0.9288 0.7298 -0.250 0.1994 0.02576 0.02064 -0.0609 0.9233 0.7321 0.000 0.2337 0.02511 0.02002 -0.0609 0.9108 0.7349 0.250 0.2960 0.02399 0.01892 -0.0661 0.9053 0.7377 0.500 0.3302 0.02337 0.01833 -0.0670 0.8930 0.7412 0.750 0.3983 0.02210 0.01710 -0.0741 0.8887 0.7446 1.000 0.4406 0.02138 0.01641 -0.0771 0.8768 0.7481 1.250 0.4907 0.02013 0.01522 -0.0797 0.8708 0.7498 1.500 0.5187 0.01939 0.01454 -0.0785 0.8541 0.7518 1.750 0.5465 0.01879 0.01399 -0.0776 0.8319 0.7541 2.000 0.5836 0.01814 0.01333 -0.0785 0.7990 0.7565 2.250 0.6320 0.01757 0.01247 -0.0816 0.7097 0.7589 2.500 0.6544 0.01847 0.01230 -0.0802 0.5224 0.7620 2.750 0.6694 0.01988 0.01278 -0.0789 0.3572 0.7647 3.000 0.6839 0.02100 0.01318 -0.0772 0.2335 0.7659 3.250 0.7002 0.02173 0.01352 -0.0753 0.1782 0.7670 3.500 0.7204 0.02225 0.01388 -0.0740 0.1524 0.7683 3.750 0.7410 0.02276 0.01429 -0.0727 0.1372 0.7700 4.000 0.7633 0.02335 0.01478 -0.0718 0.1266 0.7718 4.250 0.7898 0.02375 0.01516 -0.0719 0.1178 0.7732 4.500 0.8163 0.02436 0.01572 -0.0721 0.1108 0.7744 4.750 0.8444 0.02482 0.01615 -0.0725 0.1047 0.7758 5.000 0.8730 0.02559 0.01685 -0.0732 0.0995 0.7772 5.250 0.9031 0.02609 0.01737 -0.0740 0.0947 0.7787 5.500 0.9349 0.02696 0.01812 -0.0755 0.0902 0.7808 5.750 0.9700 0.02780 0.01901 -0.0774 0.0864 0.7827 6.000 0.9942 0.02825 0.01950 -0.0768 0.0829 0.7837 6.250 1.0200 0.02897 0.02015 -0.0767 0.0798 0.7848 6.500 1.0471 0.02988 0.02114 -0.0767 0.0770 0.7860 6.750 1.0734 0.03060 0.02197 -0.0765 0.0742 0.7872 7.000 1.1001 0.03135 0.02271 -0.0766 0.0717 0.7886 7.250 1.1302 0.03281 0.02414 -0.0775 0.0691 0.7900 7.500 1.1549 0.03364 0.02520 -0.0770 0.0668 0.7916 7.750 1.1814 0.03468 0.02634 -0.0771 0.0647 0.7936 8.000 1.2088 0.03578 0.02749 -0.0775 0.0630 0.7958 8.250 1.2418 0.03806 0.02969 -0.0793 0.0613 0.7976 8.500 1.2629 0.03939 0.03141 -0.0786 0.0599 0.7992 8.750 1.2808 0.04088 0.03322 -0.0771 0.0584 0.8004 9.000 1.2979 0.04222 0.03475 -0.0756 0.0570 0.8016 9.250 1.3171 0.04348 0.03609 -0.0745 0.0559 0.8030 9.500 1.3365 0.04495 0.03763 -0.0737 0.0550 0.8045 9.750 1.3557 0.04740 0.04015 -0.0732 0.0541 0.8061 10.000 1.3609 0.05026 0.04340 -0.0704 0.0536 0.8076 10.250 1.3597 0.05315 0.04674 -0.0668 0.0532 0.8093 10.500 1.3522 0.05640 0.05043 -0.0626 0.0529 0.8112 10.750 1.3375 0.05973 0.05414 -0.0579 0.0526 0.8130 11.000 1.3171 0.06320 0.05795 -0.0530 0.0524 0.8145 11.250 1.2942 0.06740 0.06248 -0.0491 0.0524 0.8157 11.500 1.2664 0.07199 0.06739 -0.0457 0.0524 0.8166 11.750 1.2363 0.07714 0.07282 -0.0434 0.0525 0.8173 12.000 1.2039 0.08311 0.07906 -0.0427 0.0527 0.8180 12.250 1.1699 0.09005 0.08623 -0.0439 0.0530 0.8186 12.500 1.1393 0.09770 0.09407 -0.0469 0.0534 0.8192 12.750 1.1127 0.10597 0.10248 -0.0512 0.0537 0.8198