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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.8101 0.07460 0.06760 -0.0645 1.0000 0.0516 -13.750 -0.8474 0.06704 0.05976 -0.0680 1.0000 0.0516 -13.500 -0.8715 0.06184 0.05433 -0.0694 1.0000 0.0519 -13.250 -0.8895 0.05774 0.05001 -0.0697 1.0000 0.0523 -13.000 -0.9044 0.05431 0.04636 -0.0692 1.0000 0.0528 -12.750 -0.9181 0.05136 0.04318 -0.0679 1.0000 0.0535 -12.500 -0.9323 0.04881 0.04040 -0.0657 1.0000 0.0541 -12.250 -0.9476 0.04661 0.03795 -0.0626 1.0000 0.0548 -12.000 -0.9447 0.04508 0.03639 -0.0608 1.0000 0.0556 -11.750 -0.9388 0.04381 0.03510 -0.0593 1.0000 0.0564 -11.500 -0.9329 0.04246 0.03369 -0.0578 1.0000 0.0574 -11.250 -0.9262 0.04101 0.03212 -0.0563 1.0000 0.0585 -11.000 -0.9183 0.03948 0.03043 -0.0548 1.0000 0.0598 -10.750 -0.9090 0.03792 0.02865 -0.0533 1.0000 0.0612 -10.500 -0.8976 0.03652 0.02707 -0.0518 1.0000 0.0626 -10.250 -0.8838 0.03558 0.02618 -0.0505 1.0000 0.0640 -10.000 -0.8698 0.03463 0.02520 -0.0493 1.0000 0.0658 -9.750 -0.8551 0.03360 0.02406 -0.0481 1.0000 0.0679 -9.500 -0.8394 0.03253 0.02278 -0.0469 1.0000 0.0702 -9.250 -0.8230 0.03160 0.02188 -0.0457 1.0000 0.0720 -9.000 -0.8061 0.03079 0.02111 -0.0447 1.0000 0.0741 -8.750 -0.7885 0.03000 0.02026 -0.0437 1.0000 0.0770 -8.500 -0.7700 0.02923 0.01934 -0.0427 1.0000 0.0800 -8.250 -0.7518 0.02846 0.01866 -0.0419 1.0000 0.0825 -8.000 -0.7324 0.02779 0.01800 -0.0412 1.0000 0.0859 -7.750 -0.7121 0.02718 0.01729 -0.0405 1.0000 0.0897 -7.500 -0.6918 0.02648 0.01666 -0.0400 1.0000 0.0931 -7.250 -0.6686 0.02588 0.01608 -0.0400 0.9995 0.0977 -7.000 -0.6371 0.02526 0.01542 -0.0415 0.9969 0.1032 -6.750 -0.6051 0.02461 0.01486 -0.0432 0.9944 0.1093 -6.500 -0.5729 0.02407 0.01431 -0.0448 0.9921 0.1165 -6.250 -0.5420 0.02349 0.01380 -0.0463 0.9893 0.1246 -6.000 -0.5098 0.02293 0.01332 -0.0480 0.9865 0.1350 -5.750 -0.4760 0.02240 0.01286 -0.0500 0.9839 0.1488 -5.500 -0.4406 0.02183 0.01244 -0.0525 0.9817 0.1691 -5.250 -0.4057 0.02119 0.01202 -0.0550 0.9795 0.2018 -5.000 -0.3708 0.02039 0.01155 -0.0579 0.9769 0.2574 -4.750 -0.3313 0.01933 0.01114 -0.0621 0.9753 0.3658 -4.500 -0.3063 0.01953 0.01215 -0.0607 0.9717 0.4807 -4.250 -0.2767 0.02014 0.01289 -0.0602 0.9683 0.5423 -4.000 -0.2431 0.02038 0.01305 -0.0616 0.9648 0.5766 -3.750 -0.2119 0.02066 0.01326 -0.0624 0.9608 0.5979 -3.500 -0.1808 0.02109 0.01363 -0.0628 0.9574 0.6145 -3.250 -0.1482 0.02159 0.01409 -0.0633 0.9544 0.6301 -3.000 -0.1278 0.02231 0.01483 -0.0607 0.9491 0.6404 -2.750 -0.1027 0.02284 0.01536 -0.0595 0.9441 0.6513 -2.500 -0.0718 0.02329 0.01578 -0.0596 0.9407 0.6639 -2.250 -0.0438 0.02389 0.01638 -0.0586 0.9377 0.6738 -2.000 -0.0254 0.02427 0.01679 -0.0563 0.9308 0.6819 -1.750 0.0041 0.02445 0.01695 -0.0564 0.9267 0.6879 -1.500 0.0428 0.02435 0.01682 -0.0592 0.9240 0.6944 -1.250 0.0688 0.02450 0.01699 -0.0585 0.9197 0.6976 -1.000 0.0945 0.02457 0.01707 -0.0582 0.9136 0.7015 -0.750 0.1339 0.02441 0.01690 -0.0609 0.9093 0.7064 -0.500 0.1779 0.02417 0.01667 -0.0642 0.9060 0.7107 -0.250 0.1999 0.02417 0.01671 -0.0628 0.8960 0.7131 0.000 0.2402 0.02390 0.01648 -0.0650 0.8913 0.7154 0.250 0.2721 0.02367 0.01629 -0.0657 0.8819 0.7180 0.500 0.3257 0.02282 0.01546 -0.0696 0.8729 0.7210 0.750 0.3684 0.02204 0.01470 -0.0720 0.8567 0.7247 1.000 0.4001 0.02158 0.01431 -0.0719 0.8413 0.7268 1.250 0.4316 0.02112 0.01389 -0.0716 0.8241 0.7288 1.500 0.4653 0.02059 0.01339 -0.0717 0.8025 0.7308 1.750 0.4935 0.02027 0.01312 -0.0712 0.7747 0.7329 2.000 0.5264 0.01990 0.01275 -0.0715 0.7410 0.7352 2.250 0.5620 0.01955 0.01226 -0.0722 0.6808 0.7379 2.500 0.5981 0.01972 0.01159 -0.0729 0.5207 0.7411 2.750 0.6148 0.02068 0.01182 -0.0707 0.3961 0.7431 3.000 0.6325 0.02154 0.01218 -0.0690 0.3046 0.7449 3.250 0.6532 0.02228 0.01256 -0.0680 0.2423 0.7468 3.500 0.6763 0.02291 0.01294 -0.0675 0.2006 0.7489 3.750 0.7008 0.02347 0.01334 -0.0672 0.1718 0.7511 4.000 0.7264 0.02404 0.01378 -0.0672 0.1518 0.7536 4.250 0.7533 0.02462 0.01428 -0.0675 0.1371 0.7563 4.500 0.7794 0.02523 0.01482 -0.0676 0.1265 0.7590 4.750 0.8010 0.02577 0.01535 -0.0665 0.1183 0.7609 5.000 0.8232 0.02637 0.01596 -0.0656 0.1115 0.7631 5.250 0.8464 0.02696 0.01655 -0.0649 0.1054 0.7655 5.500 0.8703 0.02768 0.01724 -0.0645 0.1006 0.7679 5.750 0.8958 0.02834 0.01794 -0.0644 0.0956 0.7707 6.000 0.9215 0.02913 0.01866 -0.0645 0.0914 0.7738 6.250 0.9468 0.02987 0.01949 -0.0643 0.0874 0.7763 6.500 0.9693 0.03057 0.02023 -0.0635 0.0837 0.7782 6.750 0.9918 0.03139 0.02100 -0.0629 0.0807 0.7803 7.000 1.0165 0.03224 0.02200 -0.0625 0.0775 0.7826 7.250 1.0409 0.03310 0.02293 -0.0622 0.0743 0.7851 7.500 1.0654 0.03403 0.02384 -0.0621 0.0719 0.7879 7.750 1.0917 0.03520 0.02508 -0.0623 0.0695 0.7911 8.000 1.1141 0.03625 0.02634 -0.0616 0.0669 0.7935 8.250 1.1345 0.03721 0.02740 -0.0606 0.0647 0.7959 8.500 1.1556 0.03822 0.02839 -0.0600 0.0630 0.7985 8.750 1.1774 0.03965 0.03002 -0.0594 0.0613 0.8011 9.000 1.1981 0.04122 0.03185 -0.0587 0.0595 0.8039 9.250 1.2181 0.04268 0.03349 -0.0581 0.0578 0.8067 9.500 1.2365 0.04395 0.03485 -0.0573 0.0565 0.8094 9.750 1.2530 0.04513 0.03604 -0.0560 0.0554 0.8118 10.000 1.2631 0.04708 0.03835 -0.0539 0.0540 0.8147 10.250 1.2709 0.04922 0.04085 -0.0518 0.0528 0.8178 10.500 1.2777 0.05139 0.04330 -0.0497 0.0518 0.8210 10.750 1.2805 0.05351 0.04566 -0.0472 0.0510 0.8242 11.000 1.2814 0.05561 0.04799 -0.0446 0.0504 0.8267 11.250 1.2818 0.05776 0.05033 -0.0422 0.0498 0.8293 11.500 1.2825 0.05995 0.05267 -0.0401 0.0493 0.8320 11.750 1.2841 0.06217 0.05502 -0.0385 0.0488 0.8349 12.000 1.2768 0.06529 0.05835 -0.0367 0.0484 0.8377 12.250 1.2516 0.07015 0.06363 -0.0349 0.0480 0.8400 12.500 1.2224 0.07581 0.06969 -0.0343 0.0478 0.8419 12.750 1.1886 0.08257 0.07681 -0.0353 0.0477 0.8435 13.000 1.1485 0.09130 0.08589 -0.0388 0.0478 0.8447 13.250 1.0977 0.10389 0.09882 -0.0468 0.0480 0.8454