XFOIL Version 6.96 Calculated polar for: EPPLER 542 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4542 0.08802 0.08463 -0.0676 1.0000 0.0500 -11.000 -0.4625 0.08403 0.08067 -0.0679 1.0000 0.0492 -10.750 -0.4956 0.07886 0.07544 -0.0687 1.0000 0.0496 -10.500 -0.5130 0.07564 0.07224 -0.0673 1.0000 0.0491 -10.250 -0.5560 0.07341 0.06998 -0.0628 1.0000 0.0497 -8.250 -0.5486 0.03590 0.02935 -0.0601 0.9324 0.0303 -8.000 -0.5122 0.03079 0.02357 -0.0613 0.9287 0.0255 -7.750 -0.4658 0.02755 0.02005 -0.0647 0.9258 0.0246 -7.500 -0.4133 0.02489 0.01712 -0.0687 0.9218 0.0243 -7.250 -0.3553 0.02294 0.01499 -0.0733 0.9192 0.0252 -7.000 -0.3077 0.02144 0.01346 -0.0765 0.9142 0.0267 -6.750 -0.2752 0.02041 0.01243 -0.0777 0.9047 0.0297 -6.500 -0.2482 0.01951 0.01151 -0.0781 0.8950 0.0356 -6.250 -0.2334 0.01869 0.01069 -0.0763 0.8826 0.0439 -6.000 -0.2224 0.01774 0.00985 -0.0738 0.8717 0.0640 -5.750 -0.2224 0.01636 0.00899 -0.0697 0.8612 0.1486 -5.500 -0.2341 0.01519 0.00842 -0.0636 0.8488 0.2635 -5.250 -0.2567 0.01420 0.00795 -0.0552 0.8376 0.3739 -5.000 -0.2158 0.01682 0.01203 -0.0522 0.8327 0.7028 -4.750 -0.2139 0.01754 0.01262 -0.0467 0.8248 0.7283 -4.500 -0.1449 0.02035 0.01520 -0.0507 0.8201 0.7472 -4.250 -0.1009 0.02168 0.01632 -0.0520 0.8146 0.7609 -4.000 -0.0090 0.02336 0.01773 -0.0613 0.8119 0.7657 -3.750 0.0374 0.02438 0.01862 -0.0632 0.8059 0.7794 -3.500 0.0839 0.02520 0.01931 -0.0654 0.8004 0.7943 -3.250 0.1338 0.02524 0.01918 -0.0691 0.7958 0.7994 -3.000 0.1489 0.02533 0.01922 -0.0670 0.7890 0.8103 -2.750 0.1922 0.02515 0.01891 -0.0698 0.7834 0.8147 -2.500 0.2084 0.02525 0.01892 -0.0679 0.7785 0.8257 -2.250 0.2509 0.02495 0.01856 -0.0708 0.7732 0.8299 -2.000 0.2657 0.02511 0.01867 -0.0686 0.7673 0.8413 -1.750 0.3144 0.02467 0.01813 -0.0726 0.7631 0.8464 -1.500 0.3839 0.02492 0.01831 -0.0790 0.7593 0.8835 -1.250 0.4063 0.02532 0.01871 -0.0781 0.7538 0.9012 -1.000 0.4525 0.02403 0.01737 -0.0823 0.7492 0.9051 -0.750 0.4730 0.02433 0.01760 -0.0813 0.7452 0.9164 -0.500 0.5112 0.02335 0.01664 -0.0841 0.7401 0.9203 -0.250 0.5301 0.02361 0.01689 -0.0829 0.7350 0.9310 0.000 0.5683 0.02268 0.01593 -0.0857 0.7309 0.9344 0.500 0.6241 0.02209 0.01536 -0.0872 0.7214 0.9480 0.750 0.6478 0.02231 0.01559 -0.0870 0.7168 0.9576 1.250 0.7135 0.02110 0.01441 -0.0905 0.7076 0.9673 1.500 0.7408 0.02078 0.01412 -0.0911 0.7024 0.9731 1.750 0.7748 0.02028 0.01362 -0.0931 0.6978 0.9787 2.000 0.8043 0.01993 0.01331 -0.0941 0.6922 0.9847 2.250 0.8363 0.01940 0.01285 -0.0958 0.6859 0.9897 2.750 0.9017 0.01840 0.01191 -0.0992 0.6744 0.9988 3.000 0.9258 0.01820 0.01177 -0.0991 0.6681 1.0000 3.750 0.8236 0.02159 0.01519 -0.0639 0.6536 0.9319 4.000 0.8807 0.02097 0.01457 -0.0698 0.6475 0.9467 4.250 0.9237 0.02051 0.01426 -0.0732 0.6389 0.9604 4.500 0.8199 0.02159 0.01527 -0.0487 0.6363 0.9155 4.750 0.8427 0.02132 0.01498 -0.0480 0.6310 0.9156 5.000 0.8553 0.02117 0.01497 -0.0456 0.6229 0.9144 5.250 0.8765 0.02088 0.01468 -0.0446 0.6164 0.9139 5.500 0.8825 0.02080 0.01469 -0.0408 0.6088 0.9140 5.750 0.8957 0.02058 0.01450 -0.0383 0.6016 0.9137 6.000 0.9039 0.02041 0.01440 -0.0348 0.5940 0.9131 6.250 0.9077 0.02021 0.01425 -0.0305 0.5863 0.9129 6.500 0.9045 0.02003 0.01410 -0.0246 0.5793 0.9137 6.750 0.8856 0.01979 0.01391 -0.0159 0.5720 0.9139 7.000 0.8885 0.01946 0.01358 -0.0113 0.5643 0.9144 7.250 0.8788 0.01916 0.01336 -0.0045 0.5555 0.9160 7.500 0.8909 0.01886 0.01312 -0.0017 0.5448 0.9168 7.750 0.9065 0.01854 0.01282 0.0004 0.5337 0.9175 8.000 0.9104 0.01827 0.01264 0.0046 0.5209 0.9186 8.250 0.9149 0.01804 0.01249 0.0087 0.5071 0.9198 8.500 0.9186 0.01782 0.01232 0.0129 0.4919 0.9212 8.750 0.9209 0.01765 0.01218 0.0173 0.4754 0.9234 9.000 0.9256 0.01763 0.01215 0.0210 0.4563 0.9253 9.250 0.9292 0.01780 0.01233 0.0246 0.4331 0.9270 9.500 0.9335 0.01814 0.01259 0.0278 0.4068 0.9287 9.750 0.9368 0.01869 0.01305 0.0308 0.3792 0.9303 10.000 0.9367 0.01936 0.01364 0.0343 0.3512 0.9321 10.250 0.9363 0.02022 0.01441 0.0374 0.3244 0.9342 10.500 0.9345 0.02127 0.01536 0.0404 0.2985 0.9367 10.750 0.9342 0.02242 0.01645 0.0429 0.2733 0.9396 11.000 0.9342 0.02375 0.01770 0.0450 0.2488 0.9421 11.250 0.9346 0.02520 0.01908 0.0467 0.2256 0.9443 11.500 0.9351 0.02669 0.02051 0.0484 0.2041 0.9467 11.750 0.9366 0.02827 0.02206 0.0497 0.1833 0.9494 12.000 0.9374 0.03003 0.02375 0.0508 0.1644 0.9523 12.250 0.9395 0.03183 0.02551 0.0516 0.1466 0.9553 12.500 0.9427 0.03369 0.02735 0.0521 0.1297 0.9584 12.750 0.9467 0.03570 0.02935 0.0522 0.1143 0.9615 13.000 0.9506 0.03786 0.03150 0.0521 0.1002 0.9651 13.250 0.9549 0.04018 0.03381 0.0517 0.0877 0.9693 13.500 0.9605 0.04263 0.03625 0.0508 0.0770 0.9738 13.750 0.9658 0.04516 0.03878 0.0498 0.0683 0.9794 14.000 0.9692 0.04762 0.04122 0.0491 0.0614 0.9917 14.250 0.9749 0.04984 0.04353 0.0488 0.0553 1.0000 14.500 0.9781 0.05228 0.04597 0.0485 0.0506 1.0000 14.750 0.9840 0.05463 0.04840 0.0478 0.0461 1.0000 15.000 0.9881 0.05712 0.05091 0.0473 0.0423 1.0000 15.250 0.9933 0.05965 0.05350 0.0465 0.0388 1.0000 15.500 0.9977 0.06222 0.05611 0.0460 0.0356 1.0000 15.750 1.0024 0.06494 0.05892 0.0450 0.0328 1.0000 16.000 1.0050 0.06784 0.06187 0.0441 0.0299 1.0000 16.250 1.0087 0.07077 0.06491 0.0430 0.0276 1.0000 16.500 1.0129 0.07352 0.06767 0.0423 0.0254 1.0000 16.750 1.0144 0.07689 0.07121 0.0410 0.0234 1.0000 17.000 1.0155 0.08017 0.07446 0.0396 0.0213 1.0000 17.250 1.0148 0.08399 0.07850 0.0381 0.0199 1.0000 17.500 1.0154 0.08756 0.08211 0.0363 0.0186 1.0000 17.750 1.0137 0.09149 0.08617 0.0348 0.0172 1.0000 18.000 1.0124 0.09555 0.09042 0.0331 0.0164 1.0000 18.250 1.0111 0.09962 0.09463 0.0311 0.0158 1.0000 18.500 1.0131 0.10305 0.09806 0.0294 0.0150 1.0000 18.750 1.0034 0.10866 0.10389 0.0264 0.0142 1.0000 19.000 0.9929 0.11466 0.11013 0.0231 0.0138 1.0000 19.250 0.9847 0.12035 0.11601 0.0198 0.0135 1.0000