XFOIL Version 6.96 Calculated polar for: EPPLER 326 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 -0.5163 0.08900 0.08561 -0.0245 1.0000 0.0403 -9.500 -0.5386 0.08456 0.08110 -0.0266 1.0000 0.0405 -9.250 -0.5583 0.08128 0.07773 -0.0259 1.0000 0.0406 -9.000 -0.5794 0.07882 0.07518 -0.0232 1.0000 0.0406 -8.750 -0.5971 0.07651 0.07273 -0.0200 1.0000 0.0407 -8.500 -0.6066 0.07138 0.06754 -0.0184 1.0000 0.0411 -8.250 -0.5925 0.06658 0.06291 -0.0187 1.0000 0.0420 -8.000 -0.5896 0.06377 0.06011 -0.0171 1.0000 0.0428 -7.750 -0.5882 0.06114 0.05743 -0.0151 1.0000 0.0436 -7.500 -0.5873 0.05850 0.05472 -0.0128 1.0000 0.0450 -7.250 -0.5861 0.05590 0.05200 -0.0102 1.0000 0.0465 -7.000 -0.5962 0.05684 0.05226 -0.0034 1.0000 0.0504 -6.750 -0.5964 0.05058 0.04603 -0.0015 1.0000 0.0516 -6.500 -0.5867 0.04758 0.04311 0.0002 1.0000 0.0528 -6.250 -0.5792 0.04545 0.04098 0.0026 1.0000 0.0543 -6.000 -0.5709 0.04350 0.03896 0.0050 0.9979 0.0568 -5.750 -0.5395 0.03982 0.03478 0.0030 0.9747 0.0643 -5.500 -0.5026 0.03685 0.03174 0.0001 0.9476 0.0685 -5.250 -0.4671 0.03385 0.02833 -0.0021 0.9168 0.0786 -4.750 -0.3781 0.02172 0.01415 -0.0003 0.8627 0.0245 -4.500 -0.3460 0.02003 0.01213 -0.0002 0.8313 0.0244 -4.250 -0.3170 0.01883 0.01067 0.0004 0.8038 0.0249 -4.000 -0.2904 0.01793 0.00956 0.0012 0.7788 0.0265 -3.750 -0.2674 0.01713 0.00873 0.0022 0.7573 0.0302 -3.500 -0.2451 0.01637 0.00785 0.0037 0.7371 0.0334 -3.250 -0.2262 0.01560 0.00706 0.0056 0.7189 0.0379 -3.000 -0.2075 0.01496 0.00635 0.0076 0.7021 0.0493 -2.750 -0.2012 0.01339 0.00542 0.0117 0.6878 0.1725 -2.500 -0.2088 0.01156 0.00630 0.0201 0.6762 0.7963 -2.250 -0.1553 0.01453 0.00905 0.0202 0.6589 0.8691 -2.000 -0.0138 0.01747 0.01147 0.0027 0.6344 0.9019 -1.750 0.0590 0.01802 0.01170 -0.0047 0.6167 0.9213 -1.500 0.0918 0.01802 0.01154 -0.0056 0.6027 0.9311 -1.250 0.1305 0.01781 0.01115 -0.0079 0.5891 0.9362 -1.000 0.1545 0.01788 0.01109 -0.0073 0.5774 0.9444 -0.750 0.1946 0.01754 0.01058 -0.0099 0.5653 0.9482 -0.500 0.2257 0.01738 0.01028 -0.0108 0.5544 0.9526 -0.250 0.2464 0.01747 0.01030 -0.0097 0.5441 0.9584 0.000 0.2829 0.01711 0.00981 -0.0118 0.5340 0.9611 0.250 0.3154 0.01691 0.00951 -0.0130 0.5243 0.9646 0.500 0.3428 0.01683 0.00937 -0.0133 0.5148 0.9684 0.750 0.3674 0.01686 0.00928 -0.0130 0.5071 0.9723 1.000 0.4014 0.01656 0.00896 -0.0146 0.4978 0.9748 1.250 0.4318 0.01645 0.00873 -0.0155 0.4901 0.9776 1.500 0.4594 0.01636 0.00865 -0.0158 0.4815 0.9805 1.750 0.4844 0.01646 0.00864 -0.0156 0.4750 0.9835 2.000 0.5158 0.01621 0.00844 -0.0167 0.4666 0.9856 2.250 0.5460 0.01612 0.00824 -0.0176 0.4600 0.9876 2.500 0.5751 0.01602 0.00821 -0.0183 0.4523 0.9900 2.750 0.6022 0.01601 0.00813 -0.0185 0.4460 0.9919 3.000 0.6295 0.01604 0.00819 -0.0188 0.4389 0.9940 3.250 0.6598 0.01592 0.00805 -0.0197 0.4321 0.9958 3.500 0.6873 0.01593 0.00807 -0.0200 0.4257 0.9971 3.750 0.7160 0.01589 0.00807 -0.0206 0.4187 0.9989 4.000 0.7432 0.01596 0.00808 -0.0209 0.4132 1.0000 4.250 0.7655 0.01605 0.00829 -0.0202 0.4063 1.0000 4.500 0.7881 0.01617 0.00838 -0.0195 0.4006 1.0000 4.750 0.8103 0.01632 0.00860 -0.0188 0.3943 1.0000 5.000 0.8326 0.01643 0.00876 -0.0180 0.3878 1.0000 5.250 0.8550 0.01662 0.00892 -0.0173 0.3824 1.0000 5.500 0.8767 0.01674 0.00917 -0.0165 0.3752 1.0000 5.750 0.8990 0.01688 0.00930 -0.0157 0.3695 1.0000 6.000 0.9204 0.01705 0.00959 -0.0148 0.3624 1.0000 6.250 0.9422 0.01718 0.00974 -0.0140 0.3559 1.0000 6.500 0.9635 0.01738 0.01001 -0.0131 0.3493 1.0000 6.750 0.9845 0.01750 0.01021 -0.0121 0.3419 1.0000 7.000 1.0056 0.01770 0.01045 -0.0112 0.3353 1.0000 7.250 1.0260 0.01782 0.01069 -0.0101 0.3274 1.0000 7.500 1.0465 0.01801 0.01092 -0.0091 0.3202 1.0000 7.750 1.0662 0.01813 0.01116 -0.0079 0.3119 1.0000 8.000 1.0855 0.01832 0.01142 -0.0067 0.3038 1.0000 8.250 1.1047 0.01846 0.01162 -0.0054 0.2954 1.0000 8.500 1.1228 0.01866 0.01197 -0.0040 0.2861 1.0000 8.750 1.1407 0.01886 0.01218 -0.0026 0.2773 1.0000 9.000 1.1573 0.01903 0.01249 -0.0009 0.2669 1.0000 9.250 1.1732 0.01927 0.01285 0.0008 0.2559 1.0000 9.500 1.1880 0.01956 0.01321 0.0027 0.2449 1.0000 9.750 1.2012 0.01989 0.01360 0.0048 0.2329 1.0000 10.000 1.2126 0.02028 0.01404 0.0072 0.2203 1.0000 10.250 1.2217 0.02075 0.01455 0.0099 0.2070 1.0000 10.500 1.2282 0.02129 0.01514 0.0129 0.1934 1.0000 10.750 1.2315 0.02190 0.01579 0.0164 0.1799 1.0000 11.000 1.2310 0.02255 0.01649 0.0205 0.1675 1.0000 11.250 1.2255 0.02322 0.01720 0.0254 0.1564 1.0000 11.500 1.2117 0.02386 0.01786 0.0317 0.1485 1.0000 11.750 1.1865 0.02423 0.01826 0.0401 0.1445 1.0000 12.000 1.1648 0.02497 0.01896 0.0470 0.1398 1.0000 12.250 1.1558 0.02616 0.02019 0.0508 0.1308 1.0000 12.500 1.1480 0.02789 0.02192 0.0531 0.1223 1.0000 12.750 1.1405 0.03007 0.02409 0.0546 0.1142 1.0000 13.000 1.1359 0.03240 0.02649 0.0553 0.1058 1.0000 13.250 1.1267 0.03532 0.02937 0.0556 0.0993 1.0000 13.500 1.1215 0.03814 0.03229 0.0555 0.0919 1.0000 13.750 1.1125 0.04139 0.03551 0.0553 0.0866 1.0000 14.000 1.1064 0.04457 0.03880 0.0548 0.0805 1.0000 14.250 1.0963 0.04805 0.04220 0.0544 0.0760 1.0000 14.500 1.0910 0.05139 0.04570 0.0535 0.0708 1.0000 14.750 1.0830 0.05489 0.04920 0.0528 0.0669 1.0000 15.000 1.0759 0.05842 0.05278 0.0520 0.0626 1.0000 15.250 1.0717 0.06178 0.05624 0.0510 0.0592 1.0000 15.500 1.0652 0.06536 0.05976 0.0501 0.0555 1.0000 15.750 1.0619 0.06874 0.06325 0.0493 0.0523 1.0000 16.000 1.0585 0.07232 0.06693 0.0480 0.0495 1.0000 16.250 1.0551 0.07583 0.07044 0.0468 0.0468 1.0000 16.500 1.0544 0.07884 0.07347 0.0462 0.0441 1.0000 16.750 1.0500 0.08285 0.07763 0.0446 0.0420 1.0000 17.000 1.0474 0.08657 0.08143 0.0430 0.0400 1.0000 17.250 1.0475 0.08972 0.08456 0.0419 0.0380 1.0000 17.500 1.0469 0.09295 0.08786 0.0412 0.0361 1.0000 17.750 1.0409 0.09752 0.09261 0.0390 0.0349 1.0000 18.000 1.0347 0.10218 0.09740 0.0367 0.0335 1.0000 18.250 1.0314 0.10636 0.10166 0.0347 0.0321 1.0000 18.500 1.0324 0.10960 0.10491 0.0333 0.0308 1.0000 18.750 1.0281 0.11369 0.10906 0.0317 0.0294 1.0000 19.000 1.0165 0.11977 0.11534 0.0284 0.0289 1.0000 19.250 1.0029 0.12635 0.12211 0.0247 0.0284 1.0000