XFOIL Version 6.96 Calculated polar for: RAE(NPL) 5213 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5591 0.08960 0.08556 -0.0257 1.0000 0.0168 -10.250 -0.5667 0.08329 0.07928 -0.0293 1.0000 0.0167 -10.000 -0.5786 0.07528 0.07131 -0.0345 1.0000 0.0165 -9.750 -0.6096 0.06329 0.05924 -0.0441 1.0000 0.0163 -9.500 -0.6378 0.05658 0.05241 -0.0485 1.0000 0.0161 -9.250 -0.6618 0.05168 0.04733 -0.0497 1.0000 0.0161 -9.000 -0.6814 0.04573 0.04103 -0.0498 1.0000 0.0161 -8.750 -0.6921 0.04015 0.03498 -0.0491 1.0000 0.0163 -8.500 -0.6959 0.03482 0.02902 -0.0478 1.0000 0.0167 -8.250 -0.6858 0.03222 0.02607 -0.0466 1.0000 0.0172 -8.000 -0.6686 0.03136 0.02519 -0.0457 1.0000 0.0177 -7.750 -0.6529 0.02988 0.02353 -0.0446 1.0000 0.0185 -7.500 -0.6383 0.02750 0.02075 -0.0433 1.0000 0.0193 -7.250 -0.6223 0.02508 0.01780 -0.0418 1.0000 0.0200 -7.000 -0.6038 0.02386 0.01651 -0.0407 1.0000 0.0205 -6.750 -0.5847 0.02282 0.01539 -0.0395 1.0000 0.0210 -6.500 -0.5653 0.02186 0.01431 -0.0383 1.0000 0.0219 -6.250 -0.5455 0.02080 0.01299 -0.0370 1.0000 0.0233 -6.000 -0.5141 0.01983 0.01202 -0.0382 0.9969 0.0244 -5.750 -0.4811 0.01887 0.01098 -0.0396 0.9932 0.0255 -5.500 -0.4487 0.01790 0.00988 -0.0407 0.9891 0.0268 -5.250 -0.4148 0.01714 0.00916 -0.0423 0.9855 0.0285 -5.000 -0.3826 0.01650 0.00846 -0.0434 0.9807 0.0305 -4.750 -0.3493 0.01576 0.00773 -0.0448 0.9764 0.0319 -4.500 -0.3160 0.01519 0.00717 -0.0462 0.9719 0.0340 -4.250 -0.2837 0.01464 0.00660 -0.0473 0.9662 0.0365 -4.000 -0.2484 0.01412 0.00609 -0.0490 0.9625 0.0391 -3.750 -0.2175 0.01366 0.00563 -0.0497 0.9556 0.0423 -3.500 -0.1833 0.01324 0.00519 -0.0511 0.9507 0.0467 -3.250 -0.1514 0.01281 0.00478 -0.0520 0.9443 0.0530 -3.000 -0.1190 0.01235 0.00439 -0.0530 0.9379 0.0675 -2.750 -0.0863 0.01173 0.00403 -0.0542 0.9321 0.1219 -2.500 -0.0586 0.01068 0.00365 -0.0550 0.9234 0.2856 -2.250 -0.0295 0.00980 0.00361 -0.0556 0.9168 0.4947 -2.000 -0.0016 0.00973 0.00376 -0.0553 0.9074 0.5717 -1.750 0.0291 0.00982 0.00395 -0.0552 0.9001 0.6240 -1.500 0.0569 0.00995 0.00410 -0.0546 0.8896 0.6550 -1.250 0.0863 0.00996 0.00411 -0.0544 0.8805 0.6681 -1.000 0.1157 0.00994 0.00401 -0.0544 0.8701 0.6752 -0.750 0.1442 0.00989 0.00395 -0.0542 0.8592 0.6797 -0.500 0.1729 0.00985 0.00385 -0.0539 0.8459 0.6850 -0.250 0.2011 0.00983 0.00375 -0.0535 0.8304 0.6906 0.000 0.2283 0.00980 0.00368 -0.0530 0.8133 0.6951 0.250 0.2553 0.00979 0.00360 -0.0523 0.7925 0.6998 0.500 0.2815 0.00980 0.00350 -0.0514 0.7618 0.7050 0.750 0.3077 0.00987 0.00340 -0.0506 0.7279 0.7103 1.000 0.3336 0.00992 0.00337 -0.0498 0.6975 0.7144 1.250 0.3599 0.01001 0.00336 -0.0491 0.6684 0.7193 1.500 0.3861 0.01013 0.00336 -0.0485 0.6327 0.7246 1.750 0.4112 0.01030 0.00337 -0.0476 0.5834 0.7292 2.000 0.4343 0.01063 0.00340 -0.0464 0.5097 0.7339 2.250 0.4554 0.01124 0.00354 -0.0451 0.4080 0.7393 2.750 0.4979 0.01275 0.00410 -0.0432 0.2038 0.7495 3.000 0.5218 0.01326 0.00439 -0.0426 0.1599 0.7554 3.250 0.5472 0.01364 0.00467 -0.0422 0.1396 0.7619 3.500 0.5723 0.01395 0.00495 -0.0416 0.1271 0.7675 3.750 0.5974 0.01427 0.00525 -0.0411 0.1179 0.7741 4.000 0.6228 0.01456 0.00557 -0.0406 0.1112 0.7813 4.250 0.6474 0.01489 0.00590 -0.0400 0.1053 0.7894 4.500 0.6721 0.01523 0.00626 -0.0394 0.1001 0.7982 4.750 0.6965 0.01552 0.00661 -0.0387 0.0950 0.8079 5.000 0.7202 0.01596 0.00704 -0.0380 0.0901 0.8193 5.250 0.7450 0.01620 0.00739 -0.0373 0.0852 0.8342 5.500 0.7684 0.01650 0.00774 -0.0365 0.0806 0.8557 5.750 0.7922 0.01675 0.00813 -0.0356 0.0764 0.8976 6.000 0.8222 0.01707 0.00851 -0.0362 0.0719 1.0000 6.250 0.8474 0.01755 0.00897 -0.0359 0.0681 1.0000 6.500 0.8728 0.01797 0.00942 -0.0356 0.0641 1.0000 6.750 0.8973 0.01846 0.00988 -0.0352 0.0609 1.0000 7.000 0.9220 0.01894 0.01041 -0.0348 0.0573 1.0000 7.250 0.9459 0.01948 0.01092 -0.0343 0.0546 1.0000 7.500 0.9697 0.02008 0.01159 -0.0337 0.0516 1.0000 7.750 0.9931 0.02064 0.01216 -0.0332 0.0491 1.0000 8.000 1.0158 0.02132 0.01287 -0.0325 0.0468 1.0000 8.250 1.0385 0.02199 0.01361 -0.0319 0.0446 1.0000 8.500 1.0605 0.02268 0.01430 -0.0312 0.0429 1.0000 8.750 1.0819 0.02353 0.01522 -0.0304 0.0415 1.0000 9.000 1.1031 0.02441 0.01620 -0.0295 0.0400 1.0000 9.250 1.1239 0.02527 0.01713 -0.0287 0.0388 1.0000 9.500 1.1440 0.02612 0.01802 -0.0278 0.0379 1.0000 9.750 1.1631 0.02712 0.01908 -0.0269 0.0369 1.0000 10.000 1.1823 0.02822 0.02035 -0.0259 0.0359 1.0000 10.250 1.2005 0.02929 0.02156 -0.0248 0.0349 1.0000 10.500 1.2178 0.03035 0.02272 -0.0237 0.0341 1.0000 10.750 1.2342 0.03142 0.02386 -0.0225 0.0335 1.0000 11.000 1.2494 0.03257 0.02509 -0.0213 0.0330 1.0000 11.250 1.2629 0.03394 0.02655 -0.0199 0.0326 1.0000 11.500 1.2736 0.03558 0.02843 -0.0182 0.0321 1.0000 11.750 1.2808 0.03730 0.03038 -0.0161 0.0317 1.0000 12.000 1.2853 0.03911 0.03242 -0.0139 0.0313 1.0000 12.250 1.2877 0.04106 0.03457 -0.0118 0.0309 1.0000 12.500 1.2879 0.04313 0.03684 -0.0098 0.0306 1.0000 12.750 1.2864 0.04538 0.03928 -0.0082 0.0303 1.0000 13.000 1.2833 0.04783 0.04191 -0.0069 0.0300 1.0000 13.250 1.2785 0.05059 0.04486 -0.0061 0.0298 1.0000 13.500 1.2725 0.05362 0.04805 -0.0058 0.0295 1.0000 13.750 1.2641 0.05718 0.05178 -0.0061 0.0294 1.0000 14.000 1.2543 0.06117 0.05594 -0.0071 0.0292 1.0000 14.250 1.2385 0.06639 0.06136 -0.0091 0.0291 1.0000 14.500 1.2199 0.07251 0.06769 -0.0123 0.0290 1.0000 14.750 1.1702 0.08542 0.08099 -0.0210 0.0291 1.0000