XFOIL Version 6.96 Calculated polar for: NACA 2412 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.6309 0.07906 0.07523 -0.0460 1.0000 0.0578 -11.000 -0.6470 0.07081 0.06694 -0.0515 1.0000 0.0563 -10.750 -0.6836 0.06148 0.05751 -0.0592 1.0000 0.0552 -10.500 -0.7222 0.05571 0.05159 -0.0599 1.0000 0.0544 -10.250 -0.7548 0.05015 0.04576 -0.0582 1.0000 0.0538 -10.000 -0.7768 0.04535 0.04060 -0.0553 1.0000 0.0536 -9.750 -0.7869 0.04159 0.03649 -0.0523 1.0000 0.0540 -9.500 -0.7902 0.03850 0.03301 -0.0494 1.0000 0.0550 -9.250 -0.7886 0.03584 0.02995 -0.0465 1.0000 0.0560 -9.000 -0.7827 0.03372 0.02742 -0.0437 1.0000 0.0569 -8.750 -0.7748 0.03126 0.02459 -0.0413 1.0000 0.0577 -8.500 -0.7612 0.02919 0.02246 -0.0397 1.0000 0.0591 -8.250 -0.7451 0.02818 0.02139 -0.0381 1.0000 0.0607 -8.000 -0.7287 0.02707 0.02016 -0.0365 1.0000 0.0622 -7.750 -0.7120 0.02579 0.01868 -0.0348 1.0000 0.0636 -7.500 -0.6943 0.02467 0.01734 -0.0333 1.0000 0.0652 -7.250 -0.6759 0.02383 0.01627 -0.0318 1.0000 0.0668 -7.000 -0.6567 0.02232 0.01461 -0.0306 1.0000 0.0685 -6.750 -0.6366 0.02134 0.01363 -0.0295 1.0000 0.0703 -6.500 -0.6161 0.02064 0.01289 -0.0284 1.0000 0.0723 -6.250 -0.5953 0.02005 0.01222 -0.0274 1.0000 0.0750 -6.000 -0.5737 0.01956 0.01160 -0.0264 1.0000 0.0778 -5.750 -0.5515 0.01862 0.01066 -0.0257 1.0000 0.0809 -5.500 -0.5215 0.01805 0.01012 -0.0265 0.9983 0.0853 -5.250 -0.4810 0.01744 0.00944 -0.0293 0.9945 0.0921 -5.000 -0.4426 0.01682 0.00888 -0.0318 0.9899 0.1027 -4.750 -0.4028 0.01619 0.00830 -0.0345 0.9856 0.1178 -4.500 -0.3645 0.01559 0.00779 -0.0369 0.9808 0.1367 -4.250 -0.3259 0.01510 0.00743 -0.0395 0.9753 0.1586 -4.000 -0.2847 0.01468 0.00713 -0.0424 0.9712 0.1855 -3.750 -0.2495 0.01427 0.00686 -0.0442 0.9641 0.2172 -3.500 -0.2077 0.01384 0.00664 -0.0472 0.9600 0.2630 -3.250 -0.1739 0.01346 0.00645 -0.0486 0.9524 0.3108 -3.000 -0.1339 0.01300 0.00622 -0.0512 0.9475 0.3634 -2.750 -0.0915 0.01251 0.00599 -0.0543 0.9440 0.4229 -2.500 -0.0617 0.01209 0.00584 -0.0546 0.9346 0.4848 -2.250 -0.0238 0.01158 0.00565 -0.0563 0.9300 0.5641 -2.000 0.0038 0.01123 0.00555 -0.0558 0.9201 0.6325 -1.750 0.0373 0.01081 0.00538 -0.0562 0.9141 0.7014 -1.500 0.0627 0.01054 0.00532 -0.0549 0.9033 0.7617 -1.250 0.0931 0.01028 0.00521 -0.0543 0.8961 0.8189 -1.000 0.1195 0.01017 0.00518 -0.0528 0.8846 0.8688 -0.750 0.1515 0.01013 0.00516 -0.0525 0.8741 0.9129 -0.500 0.1930 0.01007 0.00505 -0.0542 0.8653 0.9446 -0.250 0.2372 0.01006 0.00497 -0.0569 0.8524 0.9643 0.000 0.2860 0.01001 0.00485 -0.0608 0.8392 0.9789 0.250 0.3359 0.00994 0.00469 -0.0650 0.8247 0.9917 0.500 0.3796 0.00985 0.00451 -0.0682 0.8082 1.0000 0.750 0.4025 0.00981 0.00436 -0.0672 0.7901 1.0000 1.000 0.4257 0.00980 0.00424 -0.0662 0.7719 1.0000 1.250 0.4491 0.00982 0.00415 -0.0652 0.7537 1.0000 1.500 0.4727 0.00988 0.00410 -0.0642 0.7356 1.0000 1.750 0.4959 0.00996 0.00409 -0.0631 0.7163 1.0000 2.000 0.5193 0.01005 0.00410 -0.0621 0.6973 1.0000 2.250 0.5428 0.01017 0.00413 -0.0611 0.6786 1.0000 2.500 0.5663 0.01030 0.00417 -0.0601 0.6604 1.0000 2.750 0.5899 0.01045 0.00424 -0.0592 0.6427 1.0000 3.000 0.6136 0.01062 0.00432 -0.0582 0.6255 1.0000 3.250 0.6373 0.01080 0.00443 -0.0572 0.6088 1.0000 3.500 0.6610 0.01099 0.00456 -0.0563 0.5924 1.0000 3.750 0.6847 0.01119 0.00470 -0.0554 0.5757 1.0000 4.000 0.7080 0.01141 0.00483 -0.0543 0.5577 1.0000 4.250 0.7311 0.01161 0.00498 -0.0533 0.5375 1.0000 4.500 0.7543 0.01182 0.00515 -0.0522 0.5178 1.0000 4.750 0.7778 0.01205 0.00534 -0.0513 0.4995 1.0000 5.000 0.8010 0.01229 0.00554 -0.0503 0.4800 1.0000 5.250 0.8238 0.01256 0.00572 -0.0493 0.4589 1.0000 5.500 0.8465 0.01279 0.00593 -0.0482 0.4349 1.0000 5.750 0.8687 0.01309 0.00616 -0.0471 0.4112 1.0000 6.000 0.8911 0.01338 0.00642 -0.0461 0.3854 1.0000 6.250 0.9129 0.01373 0.00670 -0.0450 0.3582 1.0000 6.500 0.9339 0.01415 0.00702 -0.0438 0.3278 1.0000 6.750 0.9541 0.01465 0.00740 -0.0425 0.2937 1.0000 7.000 0.9731 0.01526 0.00785 -0.0411 0.2573 1.0000 7.250 0.9908 0.01600 0.00841 -0.0396 0.2186 1.0000 7.500 1.0067 0.01693 0.00909 -0.0378 0.1782 1.0000 7.750 1.0218 0.01795 0.00991 -0.0360 0.1446 1.0000 8.000 1.0370 0.01896 0.01076 -0.0341 0.1225 1.0000 8.250 1.0523 0.01995 0.01166 -0.0323 0.1086 1.0000 8.500 1.0679 0.02091 0.01261 -0.0305 0.0995 1.0000 9.000 1.0982 0.02292 0.01462 -0.0268 0.0875 1.0000 9.250 1.1137 0.02387 0.01556 -0.0251 0.0830 1.0000 9.500 1.1282 0.02523 0.01687 -0.0234 0.0794 1.0000 9.750 1.1448 0.02608 0.01784 -0.0218 0.0764 1.0000 10.000 1.1606 0.02701 0.01883 -0.0201 0.0733 1.0000 10.250 1.1764 0.02814 0.01993 -0.0187 0.0705 1.0000 10.500 1.1960 0.02971 0.02152 -0.0179 0.0678 1.0000 10.750 1.2108 0.03066 0.02263 -0.0162 0.0656 1.0000 11.000 1.2253 0.03171 0.02378 -0.0146 0.0632 1.0000 11.250 1.2401 0.03283 0.02494 -0.0132 0.0610 1.0000 11.500 1.2632 0.03501 0.02707 -0.0133 0.0582 1.0000 11.750 1.2711 0.03605 0.02834 -0.0109 0.0568 1.0000 12.000 1.2809 0.03736 0.02983 -0.0090 0.0549 1.0000 12.250 1.2900 0.03870 0.03129 -0.0072 0.0530 1.0000 12.500 1.3004 0.04002 0.03266 -0.0058 0.0513 1.0000 12.750 1.3189 0.04267 0.03530 -0.0055 0.0491 1.0000 13.000 1.3172 0.04432 0.03723 -0.0029 0.0482 1.0000 13.250 1.3163 0.04631 0.03947 -0.0008 0.0469 1.0000 13.500 1.3164 0.04839 0.04175 0.0008 0.0456 1.0000 13.750 1.3172 0.05044 0.04393 0.0021 0.0443 1.0000 14.000 1.3198 0.05245 0.04601 0.0031 0.0432 1.0000 14.250 1.3283 0.05480 0.04836 0.0038 0.0419 1.0000 14.500 1.3192 0.05878 0.05258 0.0048 0.0411 1.0000 14.750 1.3035 0.06249 0.05658 0.0053 0.0407 1.0000 15.000 1.2862 0.06682 0.06119 0.0051 0.0403 1.0000 15.250 1.2670 0.07177 0.06641 0.0041 0.0399 1.0000 15.500 1.2455 0.07741 0.07232 0.0024 0.0396 1.0000 15.750 1.2213 0.08386 0.07902 -0.0002 0.0395 1.0000 16.000 1.1937 0.09137 0.08677 -0.0038 0.0395 1.0000 16.250 1.1620 0.10031 0.09595 -0.0088 0.0397 1.0000 16.500 1.1260 0.11085 0.10672 -0.0151 0.0401 1.0000 16.750 1.0857 0.12339 0.11946 -0.0231 0.0406 1.0000 17.000 1.0415 0.13812 0.13433 -0.0322 0.0413 1.0000