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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.2281 0.08617 0.08355 -0.0574 0.7200 0.0096 -9.500 -0.2294 0.08261 0.07991 -0.0588 0.6987 0.0096 -9.250 -0.2318 0.07886 0.07612 -0.0605 0.6817 0.0097 -9.000 -0.2363 0.07479 0.07202 -0.0628 0.6672 0.0097 -8.750 -0.2497 0.06970 0.06691 -0.0668 0.6558 0.0097 -8.500 -0.2649 0.06563 0.06278 -0.0680 0.6443 0.0098 -8.250 -0.2807 0.06223 0.05931 -0.0669 0.6337 0.0097 -8.000 -0.2956 0.05948 0.05649 -0.0641 0.6239 0.0098 -7.750 -0.3011 0.05640 0.05331 -0.0624 0.6137 0.0097 -7.500 -0.3040 0.05331 0.05010 -0.0605 0.6047 0.0098 -7.250 -0.3040 0.05022 0.04688 -0.0584 0.5952 0.0100 -7.000 -0.3010 0.04727 0.04378 -0.0563 0.5863 0.0101 -6.750 -0.2971 0.04403 0.04037 -0.0539 0.5777 0.0104 -6.500 -0.2909 0.04061 0.03676 -0.0512 0.5698 0.0108 -6.250 -0.2843 0.03462 0.03033 -0.0465 0.5633 0.0114 -5.750 -0.2719 0.02859 0.02385 -0.0406 0.5472 0.0118 -4.750 -0.2086 0.01698 0.01077 -0.0301 0.5178 0.0084 -4.500 -0.1846 0.01489 0.00836 -0.0289 0.5103 0.0079 -4.250 -0.1594 0.01366 0.00691 -0.0281 0.5022 0.0077 -4.000 -0.1342 0.01290 0.00603 -0.0274 0.4949 0.0076 -3.750 -0.1098 0.01234 0.00535 -0.0265 0.4868 0.0079 -3.500 -0.0850 0.01192 0.00486 -0.0257 0.4801 0.0082 -3.250 -0.0605 0.01157 0.00444 -0.0249 0.4733 0.0084 -3.000 -0.0372 0.01116 0.00395 -0.0239 0.4668 0.0091 -2.750 -0.0127 0.01085 0.00362 -0.0231 0.4612 0.0097 -2.500 0.0124 0.01069 0.00342 -0.0225 0.4550 0.0105 -2.250 0.0375 0.01052 0.00320 -0.0218 0.4491 0.0111 -2.000 0.0624 0.01028 0.00293 -0.0211 0.4439 0.0117 -1.750 0.0873 0.01012 0.00274 -0.0205 0.4382 0.0130 -1.500 0.1123 0.00998 0.00257 -0.0198 0.4328 0.0153 -1.250 0.1380 0.00982 0.00243 -0.0193 0.4287 0.0208 -1.000 0.1621 0.00958 0.00229 -0.0184 0.4241 0.0482 -0.750 0.1859 0.00939 0.00222 -0.0177 0.4195 0.0946 -0.500 0.2051 0.00885 0.00214 -0.0161 0.4155 0.2454 -0.250 0.1905 0.00668 0.00195 -0.0079 0.4135 0.8035 0.000 0.2131 0.00695 0.00233 -0.0062 0.4096 0.8753 0.250 0.2372 0.00724 0.00255 -0.0050 0.4055 0.8929 0.500 0.2598 0.00743 0.00272 -0.0034 0.4009 0.9064 0.750 0.2831 0.00751 0.00280 -0.0020 0.3982 0.9167 1.000 0.3074 0.00758 0.00285 -0.0010 0.3953 0.9238 1.250 0.3321 0.00782 0.00308 0.0003 0.3919 0.9302 1.500 0.3588 0.00816 0.00339 0.0011 0.3884 0.9350 1.750 0.3862 0.00841 0.00357 0.0014 0.3840 0.9381 2.000 0.4104 0.00837 0.00351 0.0020 0.3817 0.9401 2.250 0.4377 0.00839 0.00350 0.0021 0.3793 0.9409 2.500 0.4654 0.00843 0.00352 0.0020 0.3764 0.9414 2.750 0.4926 0.00847 0.00353 0.0021 0.3732 0.9420 3.000 0.5193 0.00856 0.00357 0.0022 0.3699 0.9428 3.250 0.5454 0.00865 0.00363 0.0025 0.3666 0.9436 3.500 0.5725 0.00866 0.00364 0.0025 0.3647 0.9444 3.750 0.5993 0.00868 0.00365 0.0026 0.3622 0.9452 4.000 0.6255 0.00871 0.00367 0.0028 0.3596 0.9462 4.250 0.6510 0.00875 0.00369 0.0030 0.3570 0.9475 4.500 0.6769 0.00883 0.00374 0.0032 0.3540 0.9483 4.750 0.7027 0.00895 0.00383 0.0035 0.3504 0.9489 5.000 0.7300 0.00899 0.00389 0.0034 0.3488 0.9494 5.250 0.7571 0.00903 0.00395 0.0034 0.3466 0.9500 5.500 0.7839 0.00908 0.00401 0.0034 0.3440 0.9508 5.750 0.8101 0.00916 0.00407 0.0035 0.3414 0.9516 6.000 0.8357 0.00925 0.00416 0.0037 0.3383 0.9526 6.250 0.8600 0.00942 0.00429 0.0041 0.3345 0.9540 6.500 0.8870 0.00945 0.00436 0.0040 0.3327 0.9550 6.750 0.9136 0.00950 0.00444 0.0040 0.3303 0.9557 7.000 0.9397 0.00956 0.00452 0.0041 0.3274 0.9564 7.250 0.9651 0.00965 0.00462 0.0043 0.3242 0.9573 7.500 0.9895 0.00979 0.00475 0.0047 0.3209 0.9584 7.750 1.0146 0.00991 0.00488 0.0049 0.3177 0.9595 8.000 1.0409 0.00996 0.00498 0.0049 0.3150 0.9607 8.250 1.0668 0.01005 0.00509 0.0049 0.3117 0.9619 8.500 1.0910 0.01016 0.00521 0.0053 0.3082 0.9629 8.750 1.1132 0.01033 0.00537 0.0061 0.3038 0.9642 9.000 1.1384 0.01040 0.00550 0.0063 0.3010 0.9654 9.250 1.1631 0.01048 0.00562 0.0065 0.2971 0.9668 9.500 1.1860 0.01061 0.00576 0.0071 0.2925 0.9687 9.750 1.2069 0.01079 0.00594 0.0080 0.2879 0.9706 10.000 1.2315 0.01087 0.00608 0.0083 0.2840 0.9721 10.250 1.2538 0.01101 0.00625 0.0089 0.2787 0.9740 10.500 1.2718 0.01121 0.00645 0.0103 0.2732 0.9768 10.750 1.2965 0.01133 0.00663 0.0104 0.2677 0.9786 11.000 1.3185 0.01160 0.00689 0.0109 0.2610 0.9808 11.250 1.3424 0.01184 0.00717 0.0110 0.2550 0.9830 11.500 1.3646 0.01218 0.00751 0.0113 0.2462 0.9856 11.750 1.3916 0.01254 0.00788 0.0105 0.2371 0.9869 12.000 1.4167 0.01302 0.00835 0.0099 0.2268 0.9885 12.250 1.4402 0.01360 0.00891 0.0095 0.2151 0.9903 12.500 1.4619 0.01427 0.00954 0.0092 0.2021 0.9924 12.750 1.4822 0.01499 0.01025 0.0090 0.1893 0.9952 13.000 1.5006 0.01591 0.01113 0.0089 0.1753 0.9991 13.250 1.5017 0.01661 0.01183 0.0122 0.1667 1.0000 13.500 1.4990 0.01755 0.01277 0.0158 0.1590 1.0000 13.750 1.4964 0.01888 0.01407 0.0186 0.1486 1.0000 14.000 1.4971 0.02026 0.01547 0.0206 0.1398 1.0000 14.250 1.4959 0.02198 0.01720 0.0223 0.1323 1.0000 14.500 1.4871 0.02446 0.01965 0.0238 0.1212 1.0000 14.750 1.4883 0.02637 0.02162 0.0246 0.1162 1.0000 15.000 1.4746 0.02968 0.02491 0.0255 0.1054 1.0000 15.250 1.4716 0.03221 0.02750 0.0259 0.1018 1.0000 15.500 1.4618 0.03545 0.03078 0.0262 0.0966 1.0000 15.750 1.4545 0.03853 0.03392 0.0264 0.0923 1.0000 16.000 1.4296 0.04342 0.03880 0.0264 0.0823 1.0000 16.250 1.4330 0.04561 0.04112 0.0263 0.0852 1.0000 16.500 1.4025 0.05142 0.04689 0.0258 0.0740 1.0000 16.750 1.3935 0.05510 0.05064 0.0253 0.0712 1.0000 17.000 1.3801 0.05935 0.05493 0.0247 0.0679 1.0000 17.250 1.3737 0.06289 0.05855 0.0240 0.0670 1.0000 17.500 1.3610 0.06724 0.06295 0.0231 0.0622 1.0000 17.750 1.3471 0.07182 0.06755 0.0220 0.0585 1.0000 18.000 1.3408 0.07553 0.07132 0.0211 0.0562 1.0000 18.250 1.3291 0.08003 0.07586 0.0198 0.0520 1.0000 18.500 1.3179 0.08454 0.08039 0.0185 0.0491 1.0000