XFOIL Version 6.96 Calculated polar for: EPPLER 343 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3140 0.10006 0.09682 -0.0366 1.0000 0.0361 -9.500 -0.3210 0.09562 0.09244 -0.0406 1.0000 0.0362 -9.250 -0.3332 0.09060 0.08747 -0.0457 1.0000 0.0362 -9.000 -0.3158 0.08851 0.08545 -0.0401 1.0000 0.0367 -8.750 -0.3091 0.08611 0.08312 -0.0385 1.0000 0.0374 -8.500 -0.3115 0.08281 0.07989 -0.0394 1.0000 0.0379 -8.250 -0.3209 0.07918 0.07633 -0.0411 1.0000 0.0382 -8.000 -0.3128 0.07422 0.07137 -0.0468 0.9582 0.0390 -7.750 -0.2807 0.06710 0.06397 -0.0592 0.8906 0.0407 -7.500 -0.2904 0.06290 0.05904 -0.0622 0.8373 0.0429 -7.250 -0.2881 0.05874 0.05464 -0.0612 0.8042 0.0434 -7.000 -0.2767 0.05592 0.05174 -0.0603 0.7766 0.0440 -6.750 -0.2681 0.05367 0.04936 -0.0588 0.7544 0.0450 -6.500 -0.2609 0.05154 0.04703 -0.0570 0.7357 0.0463 -6.250 -0.2607 0.05083 0.04567 -0.0527 0.7202 0.0509 -6.000 -0.2548 0.04674 0.04142 -0.0510 0.7058 0.0519 -5.750 -0.2404 0.04410 0.03876 -0.0500 0.6910 0.0530 -5.500 -0.2266 0.04216 0.03668 -0.0485 0.6777 0.0550 -5.000 -0.2024 0.03805 0.03193 -0.0437 0.6537 0.0630 -4.750 -0.1850 0.03626 0.03001 -0.0424 0.6428 0.0653 -4.500 -0.1713 0.03506 0.02832 -0.0394 0.6322 0.0739 -4.250 -0.1519 0.03274 0.02599 -0.0386 0.6222 0.0767 -4.000 -0.1351 0.03205 0.02485 -0.0361 0.6125 0.0875 -3.750 -0.1012 0.02435 0.01606 -0.0321 0.6063 0.0340 -3.500 -0.0760 0.02293 0.01431 -0.0310 0.5964 0.0348 -3.250 -0.0491 0.02170 0.01277 -0.0301 0.5876 0.0352 -3.000 -0.0203 0.02031 0.01117 -0.0297 0.5784 0.0350 -2.750 0.0091 0.01920 0.00986 -0.0294 0.5708 0.0351 -2.500 0.0373 0.01831 0.00886 -0.0290 0.5623 0.0360 -2.250 0.0631 0.01740 0.00792 -0.0284 0.5557 0.0381 -2.000 0.0868 0.01687 0.00741 -0.0273 0.5478 0.0420 -1.750 0.1091 0.01637 0.00691 -0.0261 0.5410 0.0497 -1.500 0.1296 0.01580 0.00634 -0.0245 0.5349 0.0628 -1.250 0.1479 0.01334 0.00706 -0.0210 0.5287 0.8494 -1.000 0.3802 0.01632 0.00927 -0.0554 0.5127 0.9741 -0.750 0.4710 0.01528 0.00790 -0.0681 0.5042 0.9982 -0.500 0.4993 0.01516 0.00769 -0.0687 0.4985 1.0000 -0.250 0.5214 0.01516 0.00762 -0.0679 0.4934 1.0000 0.000 0.5437 0.01520 0.00754 -0.0672 0.4889 1.0000 0.250 0.5664 0.01532 0.00752 -0.0666 0.4849 1.0000 0.500 0.5885 0.01534 0.00755 -0.0658 0.4800 1.0000 0.750 0.6110 0.01540 0.00756 -0.0651 0.4754 1.0000 1.000 0.6337 0.01547 0.00753 -0.0644 0.4712 1.0000 1.250 0.6569 0.01566 0.00760 -0.0638 0.4678 1.0000 1.500 0.6791 0.01574 0.00773 -0.0630 0.4637 1.0000 1.750 0.7017 0.01585 0.00782 -0.0623 0.4595 1.0000 2.000 0.7245 0.01596 0.00788 -0.0616 0.4557 1.0000 2.250 0.7478 0.01611 0.00794 -0.0610 0.4522 1.0000 2.500 0.7705 0.01632 0.00815 -0.0603 0.4488 1.0000 2.750 0.7926 0.01648 0.00836 -0.0595 0.4450 1.0000 3.000 0.8152 0.01663 0.00851 -0.0587 0.4411 1.0000 3.250 0.8383 0.01677 0.00861 -0.0580 0.4377 1.0000 3.500 0.8619 0.01700 0.00876 -0.0575 0.4347 1.0000 3.750 0.8840 0.01726 0.00908 -0.0567 0.4316 1.0000 4.000 0.9055 0.01747 0.00937 -0.0558 0.4278 1.0000 4.250 0.9276 0.01765 0.00958 -0.0550 0.4240 1.0000 4.500 0.9505 0.01783 0.00973 -0.0543 0.4208 1.0000 4.750 0.9742 0.01808 0.00994 -0.0537 0.4181 1.0000 5.000 0.9958 0.01841 0.01032 -0.0529 0.4149 1.0000 5.250 1.0161 0.01866 0.01069 -0.0518 0.4110 1.0000 5.500 1.0373 0.01889 0.01098 -0.0508 0.4074 1.0000 5.750 1.0597 0.01911 0.01121 -0.0501 0.4043 1.0000 6.000 1.0834 0.01934 0.01139 -0.0495 0.4013 1.0000 6.250 1.1039 0.01971 0.01184 -0.0485 0.3980 1.0000 6.500 1.1224 0.02003 0.01232 -0.0471 0.3941 1.0000 6.750 1.1425 0.02028 0.01264 -0.0460 0.3903 1.0000 7.000 1.1646 0.02048 0.01283 -0.0452 0.3870 1.0000 7.250 1.1886 0.02075 0.01306 -0.0447 0.3840 1.0000 7.500 1.2047 0.02116 0.01364 -0.0430 0.3800 1.0000 7.750 1.2217 0.02149 0.01411 -0.0414 0.3758 1.0000 8.000 1.2415 0.02170 0.01435 -0.0402 0.3720 1.0000 8.250 1.2647 0.02187 0.01450 -0.0395 0.3687 1.0000 8.500 1.2827 0.02228 0.01499 -0.0381 0.3649 1.0000 8.750 1.2955 0.02266 0.01556 -0.0358 0.3603 1.0000 9.000 1.3133 0.02286 0.01583 -0.0343 0.3561 1.0000 9.250 1.3362 0.02294 0.01587 -0.0336 0.3524 1.0000 9.500 1.3510 0.02335 0.01639 -0.0316 0.3482 1.0000 9.750 1.3608 0.02370 0.01692 -0.0288 0.3432 1.0000 10.000 1.3781 0.02381 0.01707 -0.0271 0.3388 1.0000 10.250 1.4029 0.02388 0.01705 -0.0268 0.3348 1.0000 10.500 1.4040 0.02434 0.01778 -0.0225 0.3297 1.0000 10.750 1.4140 0.02452 0.01806 -0.0197 0.3247 1.0000 11.000 1.4334 0.02448 0.01798 -0.0183 0.3202 1.0000 11.250 1.4356 0.02487 0.01853 -0.0143 0.3154 1.0000 11.500 1.4363 0.02513 0.01892 -0.0099 0.3103 1.0000 11.750 1.4469 0.02510 0.01888 -0.0071 0.3055 1.0000 12.000 1.4464 0.02538 0.01925 -0.0025 0.3009 1.0000 12.250 1.4348 0.02572 0.01973 0.0038 0.2961 1.0000 12.500 1.4321 0.02578 0.01980 0.0087 0.2915 1.0000 12.750 1.4340 0.02603 0.02007 0.0126 0.2865 1.0000 13.000 1.4240 0.02671 0.02090 0.0175 0.2808 1.0000 13.250 1.4313 0.02703 0.02122 0.0199 0.2749 1.0000 13.500 1.4255 0.02811 0.02244 0.0230 0.2685 1.0000 13.750 1.4252 0.02907 0.02346 0.0252 0.2617 1.0000 14.000 1.4229 0.03042 0.02490 0.0271 0.2548 1.0000 14.250 1.4195 0.03198 0.02652 0.0287 0.2473 1.0000 14.500 1.4136 0.03401 0.02864 0.0299 0.2396 1.0000 14.750 1.4107 0.03594 0.03057 0.0307 0.2317 1.0000 15.000 1.3998 0.03882 0.03358 0.0313 0.2237 1.0000 15.250 1.3963 0.04107 0.03577 0.0317 0.2155 1.0000 15.500 1.3811 0.04474 0.03959 0.0317 0.2074 1.0000 15.750 1.3729 0.04775 0.04260 0.0317 0.1993 1.0000 16.000 1.3605 0.05141 0.04630 0.0313 0.1912 1.0000 16.250 1.3486 0.05518 0.05012 0.0308 0.1833 1.0000 16.500 1.3407 0.05851 0.05340 0.0303 0.1752 1.0000 16.750 1.3255 0.06308 0.05810 0.0291 0.1677 1.0000 17.000 1.3198 0.06633 0.06127 0.0285 0.1601 1.0000 17.250 1.3050 0.07113 0.06619 0.0271 0.1529 1.0000 17.500 1.2997 0.07453 0.06954 0.0263 0.1458 1.0000 17.750 1.2871 0.07920 0.07430 0.0247 0.1389 1.0000 18.000 1.2813 0.08286 0.07793 0.0237 0.1322 1.0000 18.250 1.2707 0.08744 0.08259 0.0220 0.1258 1.0000 18.500 1.2659 0.09108 0.08621 0.0208 0.1194 1.0000