XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0614 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 -0.9101 0.06446 0.05895 -0.0721 1.0000 0.0549 -13.750 -0.9336 0.05999 0.05429 -0.0723 1.0000 0.0549 -13.500 -0.9565 0.05625 0.05034 -0.0714 1.0000 0.0549 -13.250 -0.9794 0.05328 0.04719 -0.0690 1.0000 0.0549 -13.000 -1.0022 0.05090 0.04465 -0.0656 1.0000 0.0549 -12.750 -1.0133 0.04785 0.04141 -0.0638 1.0000 0.0552 -12.500 -1.0120 0.04534 0.03881 -0.0622 1.0000 0.0557 -12.250 -1.0066 0.04355 0.03696 -0.0607 1.0000 0.0562 -12.000 -0.9993 0.04204 0.03540 -0.0591 1.0000 0.0569 -11.750 -0.9907 0.04069 0.03399 -0.0575 1.0000 0.0577 -11.500 -0.9831 0.03922 0.03240 -0.0560 1.0000 0.0587 -11.250 -0.9753 0.03754 0.03052 -0.0546 1.0000 0.0598 -11.000 -0.9660 0.03578 0.02849 -0.0533 1.0000 0.0610 -10.750 -0.9545 0.03419 0.02656 -0.0522 1.0000 0.0621 -10.500 -0.9390 0.03234 0.02464 -0.0510 1.0000 0.0632 -10.250 -0.9217 0.03128 0.02361 -0.0500 1.0000 0.0645 -10.000 -0.9041 0.03031 0.02259 -0.0491 1.0000 0.0659 -9.750 -0.8858 0.02935 0.02153 -0.0482 1.0000 0.0677 -9.500 -0.8665 0.02844 0.02042 -0.0476 1.0000 0.0699 -9.250 -0.8477 0.02721 0.01917 -0.0466 1.0000 0.0719 -9.000 -0.8278 0.02648 0.01849 -0.0459 1.0000 0.0741 -8.750 -0.8069 0.02577 0.01773 -0.0453 1.0000 0.0766 -8.500 -0.7848 0.02511 0.01693 -0.0449 1.0000 0.0793 -8.250 -0.7641 0.02415 0.01602 -0.0441 1.0000 0.0821 -8.000 -0.7417 0.02361 0.01553 -0.0438 1.0000 0.0854 -7.750 -0.7182 0.02313 0.01498 -0.0437 1.0000 0.0891 -7.500 -0.6958 0.02236 0.01425 -0.0432 1.0000 0.0927 -7.250 -0.6721 0.02186 0.01381 -0.0432 1.0000 0.0966 -7.000 -0.6474 0.02148 0.01337 -0.0433 1.0000 0.1011 -6.750 -0.6229 0.02081 0.01279 -0.0434 1.0000 0.1060 -6.500 -0.5972 0.02042 0.01244 -0.0438 1.0000 0.1115 -6.250 -0.5702 0.01994 0.01199 -0.0444 0.9999 0.1176 -6.000 -0.5326 0.01949 0.01162 -0.0471 0.9978 0.1264 -5.750 -0.4945 0.01893 0.01116 -0.0500 0.9959 0.1373 -5.500 -0.4549 0.01838 0.01073 -0.0533 0.9944 0.1533 -5.250 -0.4124 0.01767 0.01025 -0.0575 0.9933 0.1832 -5.000 -0.3612 0.01624 0.00953 -0.0647 0.9934 0.2955 -4.750 -0.3129 0.01528 0.00987 -0.0704 0.9936 0.5282 -4.500 -0.2791 0.01573 0.01035 -0.0714 0.9905 0.5809 -4.250 -0.2485 0.01628 0.01091 -0.0716 0.9864 0.6038 -4.000 -0.2152 0.01687 0.01149 -0.0722 0.9831 0.6202 -3.750 -0.1800 0.01750 0.01208 -0.0732 0.9806 0.6334 -3.500 -0.1526 0.01792 0.01245 -0.0730 0.9754 0.6459 -3.250 -0.1296 0.01873 0.01334 -0.0708 0.9709 0.6519 -3.000 -0.0935 0.01924 0.01380 -0.0721 0.9683 0.6630 -2.750 -0.0753 0.01986 0.01448 -0.0693 0.9623 0.6672 -2.500 -0.0432 0.02027 0.01486 -0.0701 0.9583 0.6780 -2.250 -0.0223 0.02114 0.01581 -0.0669 0.9546 0.6825 -2.000 0.0107 0.02146 0.01609 -0.0681 0.9503 0.6934 -1.750 0.0258 0.02205 0.01676 -0.0640 0.9433 0.6968 -1.500 0.0554 0.02260 0.01734 -0.0629 0.9393 0.7053 -1.250 0.0760 0.02294 0.01770 -0.0606 0.9316 0.7129 -1.000 0.1070 0.02303 0.01782 -0.0603 0.9262 0.7175 -0.750 0.1564 0.02271 0.01749 -0.0648 0.9235 0.7227 -0.500 0.1884 0.02246 0.01725 -0.0656 0.9146 0.7272 -0.250 0.2385 0.02181 0.01663 -0.0683 0.9086 0.7297 0.000 0.2815 0.02123 0.01608 -0.0701 0.9011 0.7326 0.250 0.3299 0.02041 0.01528 -0.0732 0.8937 0.7361 0.500 0.3874 0.01938 0.01424 -0.0791 0.8847 0.7418 0.750 0.4181 0.01879 0.01369 -0.0782 0.8751 0.7435 1.000 0.4462 0.01834 0.01328 -0.0774 0.8627 0.7453 1.250 0.4781 0.01778 0.01275 -0.0772 0.8483 0.7472 1.500 0.5094 0.01729 0.01228 -0.0772 0.8305 0.7493 1.750 0.5407 0.01690 0.01189 -0.0774 0.8088 0.7521 2.000 0.5750 0.01653 0.01148 -0.0784 0.7796 0.7554 2.250 0.6123 0.01624 0.01105 -0.0803 0.7317 0.7587 2.500 0.6325 0.01626 0.01073 -0.0777 0.6350 0.7603 2.750 0.6414 0.01730 0.01079 -0.0735 0.4628 0.7621 3.000 0.6534 0.01845 0.01120 -0.0709 0.3268 0.7640 3.250 0.6706 0.01946 0.01164 -0.0696 0.2312 0.7660 3.500 0.6928 0.02023 0.01206 -0.0690 0.1807 0.7681 3.750 0.7185 0.02085 0.01249 -0.0692 0.1539 0.7704 4.000 0.7475 0.02147 0.01298 -0.0700 0.1376 0.7734 4.250 0.7746 0.02208 0.01348 -0.0704 0.1268 0.7759 4.500 0.7968 0.02247 0.01385 -0.0693 0.1190 0.7775 4.750 0.8198 0.02304 0.01440 -0.0684 0.1126 0.7791 5.000 0.8447 0.02347 0.01481 -0.0680 0.1068 0.7810 5.250 0.8698 0.02425 0.01550 -0.0678 0.1017 0.7830 5.500 0.8974 0.02470 0.01601 -0.0679 0.0971 0.7852 5.750 0.9255 0.02533 0.01657 -0.0684 0.0929 0.7875 6.000 0.9560 0.02626 0.01748 -0.0694 0.0890 0.7899 6.250 0.9861 0.02684 0.01811 -0.0702 0.0851 0.7922 6.500 1.0093 0.02747 0.01869 -0.0695 0.0819 0.7940 6.750 1.0343 0.02852 0.01978 -0.0689 0.0791 0.7960 7.000 1.0588 0.02923 0.02062 -0.0683 0.0763 0.7985 7.250 1.0845 0.02997 0.02139 -0.0682 0.0736 0.8011 7.500 1.1148 0.03152 0.02281 -0.0692 0.0708 0.8037 7.750 1.1406 0.03230 0.02384 -0.0691 0.0685 0.8068 8.000 1.1668 0.03333 0.02500 -0.0691 0.0663 0.8094 8.250 1.1888 0.03425 0.02600 -0.0682 0.0646 0.8115 8.500 1.2137 0.03557 0.02728 -0.0680 0.0631 0.8136 8.750 1.2350 0.03736 0.02930 -0.0672 0.0617 0.8160 9.000 1.2535 0.03882 0.03109 -0.0659 0.0602 0.8186 9.250 1.2735 0.04031 0.03279 -0.0651 0.0586 0.8213 9.500 1.2963 0.04167 0.03423 -0.0650 0.0573 0.8242 9.750 1.3150 0.04304 0.03568 -0.0639 0.0564 0.8268 10.000 1.3326 0.04495 0.03766 -0.0629 0.0555 0.8294 10.250 1.3416 0.04782 0.04083 -0.0608 0.0549 0.8321 10.500 1.3425 0.05049 0.04395 -0.0575 0.0544 0.8348 10.750 1.3384 0.05363 0.04751 -0.0540 0.0540 0.8374 11.000 1.3282 0.05703 0.05131 -0.0502 0.0537 0.8399 11.250 1.3087 0.06018 0.05481 -0.0453 0.0534 0.8422 11.500 1.2862 0.06388 0.05884 -0.0409 0.0533 0.8442 11.750 1.2595 0.06821 0.06348 -0.0375 0.0533 0.8463 12.000 1.2288 0.07334 0.06892 -0.0354 0.0534 0.8482 12.250 1.1953 0.07943 0.07530 -0.0350 0.0536 0.8500 12.500 1.1595 0.08668 0.08280 -0.0365 0.0539 0.8516 12.750 1.1221 0.09536 0.09171 -0.0404 0.0543 0.8530 13.000 1.0901 0.10480 0.10130 -0.0458 0.0547 0.8544 13.250 1.0692 0.11366 0.11024 -0.0510 0.0551 0.8559