XFOIL Version 6.96 Calculated polar for: EPPLER 335 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.5052 0.08643 0.08404 -0.0135 0.7201 0.0046 -9.750 -0.5165 0.08056 0.07814 -0.0180 0.7026 0.0045 -9.500 -0.5359 0.07450 0.07201 -0.0220 0.6885 0.0046 -9.250 -0.5555 0.07006 0.06748 -0.0224 0.6751 0.0045 -9.000 -0.5751 0.06637 0.06369 -0.0207 0.6612 0.0044 -8.750 -0.5956 0.06297 0.06019 -0.0171 0.6498 0.0043 -8.500 -0.6571 0.05196 0.04887 -0.0086 0.6512 0.0033 -8.000 -0.6665 0.04291 0.03936 -0.0009 0.6293 0.0031 -7.750 -0.7306 0.02350 0.01847 0.0143 0.6354 0.0028 -7.500 -0.7156 0.02101 0.01555 0.0166 0.6225 0.0028 -7.250 -0.6957 0.01954 0.01379 0.0180 0.6089 0.0028 -7.000 -0.6745 0.01792 0.01186 0.0194 0.5944 0.0028 -6.750 -0.6515 0.01690 0.01064 0.0203 0.5823 0.0028 -6.500 -0.6277 0.01604 0.00961 0.0211 0.5714 0.0029 -6.250 -0.6038 0.01525 0.00866 0.0220 0.5601 0.0029 -6.000 -0.5795 0.01466 0.00794 0.0227 0.5484 0.0029 -5.750 -0.5553 0.01406 0.00721 0.0235 0.5366 0.0030 -5.500 -0.5311 0.01354 0.00658 0.0242 0.5264 0.0030 -5.250 -0.5066 0.01315 0.00611 0.0249 0.5166 0.0030 -5.000 -0.4820 0.01276 0.00563 0.0257 0.5078 0.0031 -4.750 -0.4589 0.01216 0.00494 0.0267 0.4986 0.0034 -4.500 -0.4341 0.01188 0.00461 0.0273 0.4892 0.0037 -4.250 -0.4094 0.01163 0.00429 0.0280 0.4799 0.0038 -4.000 -0.3842 0.01141 0.00403 0.0286 0.4714 0.0042 -3.750 -0.3593 0.01118 0.00374 0.0293 0.4638 0.0043 -3.500 -0.3341 0.01098 0.00350 0.0299 0.4563 0.0047 -3.250 -0.3089 0.01080 0.00327 0.0305 0.4486 0.0050 -3.000 -0.2839 0.01059 0.00303 0.0311 0.4410 0.0054 -2.750 -0.2586 0.01045 0.00284 0.0317 0.4333 0.0061 -2.500 -0.2330 0.01030 0.00266 0.0322 0.4270 0.0069 -2.250 -0.2076 0.01016 0.00249 0.0328 0.4201 0.0084 -2.000 -0.1822 0.01001 0.00235 0.0333 0.4139 0.0126 -1.750 -0.1570 0.00986 0.00222 0.0339 0.4071 0.0227 -1.500 -0.1325 0.00966 0.00210 0.0345 0.4014 0.0459 -1.250 -0.1081 0.00944 0.00199 0.0352 0.3961 0.0810 -1.000 -0.0842 0.00922 0.00190 0.0360 0.3901 0.1289 -0.750 -0.0670 0.00857 0.00175 0.0379 0.3854 0.2835 -0.500 -0.0860 0.00658 0.00134 0.0472 0.3827 0.7058 -0.250 -0.0758 0.00622 0.00160 0.0516 0.3783 0.8706 0.000 -0.0499 0.00641 0.00175 0.0523 0.3734 0.8885 0.250 -0.0252 0.00655 0.00184 0.0532 0.3690 0.8984 0.500 0.0050 0.00674 0.00200 0.0530 0.3636 0.9036 0.750 0.0323 0.00695 0.00217 0.0533 0.3587 0.9103 1.000 0.0587 0.00708 0.00226 0.0538 0.3549 0.9148 1.250 0.0877 0.00714 0.00228 0.0536 0.3508 0.9159 1.500 0.1159 0.00719 0.00228 0.0535 0.3461 0.9167 1.750 0.1438 0.00725 0.00228 0.0535 0.3414 0.9174 2.000 0.1720 0.00728 0.00229 0.0534 0.3383 0.9181 2.250 0.2000 0.00732 0.00230 0.0533 0.3344 0.9189 2.500 0.2276 0.00737 0.00232 0.0533 0.3299 0.9197 2.750 0.2550 0.00743 0.00234 0.0533 0.3257 0.9204 3.000 0.2828 0.00746 0.00236 0.0533 0.3228 0.9210 3.250 0.3103 0.00750 0.00238 0.0533 0.3190 0.9218 3.500 0.3375 0.00757 0.00242 0.0533 0.3143 0.9227 3.750 0.3647 0.00764 0.00246 0.0533 0.3106 0.9235 4.000 0.3921 0.00768 0.00250 0.0533 0.3071 0.9242 4.250 0.4194 0.00773 0.00254 0.0533 0.3030 0.9249 4.500 0.4464 0.00780 0.00259 0.0533 0.2987 0.9256 4.750 0.4734 0.00787 0.00264 0.0534 0.2947 0.9263 5.000 0.5007 0.00793 0.00271 0.0533 0.2907 0.9269 5.250 0.5277 0.00801 0.00277 0.0533 0.2860 0.9275 5.500 0.5544 0.00811 0.00286 0.0534 0.2813 0.9282 5.750 0.5815 0.00818 0.00294 0.0534 0.2769 0.9288 6.000 0.6087 0.00826 0.00302 0.0533 0.2715 0.9294 6.250 0.6355 0.00838 0.00312 0.0533 0.2660 0.9301 6.500 0.6627 0.00847 0.00323 0.0532 0.2605 0.9306 6.750 0.6892 0.00860 0.00335 0.0533 0.2538 0.9312 7.000 0.7159 0.00872 0.00348 0.0533 0.2482 0.9318 7.250 0.7421 0.00887 0.00362 0.0533 0.2407 0.9325 7.500 0.7683 0.00902 0.00378 0.0534 0.2340 0.9331 7.750 0.7939 0.00921 0.00395 0.0535 0.2252 0.9338 8.000 0.8196 0.00938 0.00413 0.0536 0.2172 0.9345 8.250 0.8446 0.00960 0.00433 0.0539 0.2087 0.9353 8.500 0.8693 0.00982 0.00454 0.0541 0.1982 0.9362 8.750 0.8937 0.01007 0.00478 0.0544 0.1878 0.9370 9.000 0.9171 0.01037 0.00505 0.0548 0.1759 0.9381 9.250 0.9400 0.01068 0.00534 0.0553 0.1646 0.9393 9.500 0.9620 0.01104 0.00566 0.0559 0.1517 0.9404 9.750 0.9833 0.01144 0.00601 0.0566 0.1386 0.9415 10.000 1.0036 0.01187 0.00640 0.0574 0.1250 0.9426 10.250 1.0229 0.01234 0.00682 0.0584 0.1115 0.9437 10.500 1.0408 0.01287 0.00731 0.0595 0.0967 0.9451 10.750 1.0581 0.01340 0.00780 0.0608 0.0846 0.9466 11.000 1.0748 0.01391 0.00830 0.0621 0.0753 0.9483 11.250 1.0904 0.01443 0.00882 0.0636 0.0677 0.9502 11.500 1.1047 0.01496 0.00935 0.0652 0.0603 0.9523 11.750 1.1159 0.01547 0.00987 0.0675 0.0543 0.9550 12.250 1.1317 0.01670 0.01115 0.0726 0.0441 0.9623 12.500 1.1392 0.01756 0.01203 0.0745 0.0391 0.9668 12.750 1.1454 0.01860 0.01309 0.0761 0.0340 0.9721 13.000 1.1587 0.02010 0.01463 0.0752 0.0279 0.9757 13.250 1.1711 0.02200 0.01655 0.0735 0.0224 0.9793 13.500 1.1810 0.02430 0.01889 0.0714 0.0176 0.9831 13.750 1.1965 0.02633 0.02098 0.0689 0.0161 0.9847 14.000 1.2075 0.02899 0.02370 0.0660 0.0139 0.9863 14.250 1.2179 0.03153 0.02634 0.0636 0.0128 0.9881 14.500 1.2235 0.03451 0.02940 0.0612 0.0117 0.9904 14.750 1.2253 0.03779 0.03275 0.0590 0.0103 0.9931 15.000 1.2220 0.04155 0.03658 0.0570 0.0089 0.9991 15.250 1.2217 0.04504 0.04015 0.0550 0.0083 1.0000 15.500 1.2138 0.04811 0.04330 0.0550 0.0086 1.0000 15.750 1.2048 0.05152 0.04679 0.0546 0.0082 1.0000 16.000 1.1928 0.05543 0.05077 0.0539 0.0073 1.0000 16.250 1.1807 0.05957 0.05496 0.0529 0.0065 1.0000 16.500 1.1763 0.06293 0.05841 0.0521 0.0069 1.0000 16.750 1.1665 0.06703 0.06258 0.0509 0.0062 1.0000 17.000 1.1590 0.07092 0.06655 0.0497 0.0060 1.0000 17.250 1.1497 0.07515 0.07084 0.0484 0.0054 1.0000 17.500 1.1461 0.07865 0.07443 0.0472 0.0058 1.0000 17.750 1.1348 0.08327 0.07910 0.0457 0.0049 1.0000 18.000 1.1266 0.08754 0.08345 0.0441 0.0046 1.0000