XFOIL Version 6.96 Calculated polar for: EPPLER 330 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5331 0.09146 0.08825 0.0041 1.0000 0.0197 -8.750 -0.5389 0.08635 0.08318 0.0001 1.0000 0.0197 -8.500 -0.5486 0.08134 0.07817 -0.0034 1.0000 0.0195 -8.250 -0.5594 0.07712 0.07394 -0.0046 1.0000 0.0194 -7.250 -0.5855 0.05724 0.05347 0.0003 1.0000 0.0115 -7.000 -0.5859 0.05416 0.05030 0.0021 1.0000 0.0110 -6.750 -0.5814 0.05088 0.04687 0.0040 1.0000 0.0107 -6.500 -0.5744 0.04765 0.04348 0.0060 1.0000 0.0104 -6.000 -0.5403 0.03899 0.03398 0.0078 0.8446 0.0094 -5.750 -0.5295 0.03482 0.02927 0.0113 0.8106 0.0088 -5.500 -0.5173 0.02984 0.02354 0.0154 0.7851 0.0083 -5.250 -0.4990 0.02705 0.02018 0.0179 0.7608 0.0081 -5.000 -0.4785 0.02490 0.01756 0.0198 0.7390 0.0082 -4.750 -0.4557 0.02313 0.01541 0.0211 0.7189 0.0083 -4.500 -0.4312 0.02163 0.01358 0.0221 0.6997 0.0085 -4.250 -0.4059 0.02043 0.01210 0.0229 0.6820 0.0091 -4.000 -0.3796 0.01925 0.01067 0.0236 0.6655 0.0093 -3.750 -0.3536 0.01825 0.00948 0.0243 0.6496 0.0098 -3.500 -0.3276 0.01779 0.00882 0.0250 0.6342 0.0116 -3.250 -0.3036 0.01686 0.00784 0.0257 0.6199 0.0133 -2.750 -0.2558 0.01555 0.00627 0.0277 0.5934 0.0154 -2.500 -0.2322 0.01502 0.00560 0.0288 0.5807 0.0170 -2.250 -0.2088 0.01452 0.00502 0.0298 0.5687 0.0212 -2.000 -0.1854 0.01408 0.00451 0.0309 0.5574 0.0326 -1.750 -0.1648 0.01339 0.00410 0.0323 0.5469 0.1001 -1.500 -0.1075 0.01133 0.00508 0.0274 0.5334 0.8698 -1.250 -0.0734 0.01221 0.00577 0.0276 0.5219 0.9065 -1.000 -0.0265 0.01285 0.00616 0.0246 0.5096 0.9228 -0.750 0.0136 0.01319 0.00631 0.0226 0.4987 0.9332 -0.500 0.0480 0.01330 0.00623 0.0214 0.4889 0.9376 -0.250 0.0704 0.01336 0.00617 0.0225 0.4797 0.9436 0.000 0.1077 0.01340 0.00607 0.0206 0.4702 0.9461 0.250 0.1423 0.01344 0.00596 0.0192 0.4610 0.9490 0.500 0.1737 0.01347 0.00590 0.0184 0.4523 0.9525 0.750 0.1989 0.01355 0.00587 0.0189 0.4448 0.9568 1.000 0.2294 0.01356 0.00581 0.0183 0.4367 0.9592 1.250 0.2638 0.01357 0.00571 0.0168 0.4291 0.9614 1.500 0.2975 0.01358 0.00567 0.0155 0.4208 0.9644 1.750 0.3290 0.01365 0.00567 0.0146 0.4141 0.9685 2.000 0.3543 0.01372 0.00571 0.0150 0.4071 0.9714 2.250 0.3835 0.01374 0.00566 0.0145 0.4007 0.9729 2.500 0.4141 0.01373 0.00564 0.0138 0.3935 0.9742 2.750 0.4435 0.01376 0.00561 0.0132 0.3875 0.9756 3.000 0.4725 0.01378 0.00565 0.0128 0.3804 0.9770 3.250 0.5008 0.01384 0.00567 0.0125 0.3744 0.9786 3.500 0.5285 0.01389 0.00574 0.0123 0.3680 0.9802 3.750 0.5552 0.01397 0.00583 0.0123 0.3617 0.9817 4.000 0.5816 0.01407 0.00593 0.0124 0.3558 0.9834 4.250 0.6074 0.01417 0.00606 0.0126 0.3493 0.9847 4.500 0.6361 0.01424 0.00611 0.0122 0.3434 0.9856 4.750 0.6654 0.01429 0.00625 0.0116 0.3366 0.9868 5.000 0.6937 0.01440 0.00635 0.0112 0.3303 0.9879 5.250 0.7213 0.01448 0.00651 0.0110 0.3231 0.9889 5.500 0.7483 0.01461 0.00667 0.0109 0.3167 0.9900 5.750 0.7760 0.01473 0.00687 0.0106 0.3093 0.9913 6.000 0.8028 0.01488 0.00705 0.0105 0.3025 0.9925 6.250 0.8291 0.01502 0.00728 0.0105 0.2943 0.9935 6.500 0.8547 0.01521 0.00751 0.0107 0.2869 0.9944 6.750 0.8822 0.01534 0.00776 0.0104 0.2778 0.9954 7.000 0.9099 0.01552 0.00801 0.0100 0.2689 0.9965 7.250 0.9365 0.01573 0.00825 0.0098 0.2593 0.9975 7.500 0.9627 0.01593 0.00859 0.0097 0.2488 0.9984 7.750 0.9886 0.01618 0.00892 0.0097 0.2377 0.9993 8.000 1.0138 0.01648 0.00929 0.0097 0.2254 1.0000 8.250 1.0348 0.01683 0.00969 0.0105 0.2129 1.0000 8.500 1.0553 0.01722 0.01014 0.0114 0.1993 1.0000 8.750 1.0750 0.01768 0.01064 0.0124 0.1845 1.0000 9.000 1.0936 0.01822 0.01123 0.0135 0.1685 1.0000 9.250 1.1109 0.01885 0.01188 0.0147 0.1527 1.0000 9.500 1.1267 0.01958 0.01261 0.0161 0.1366 1.0000 9.750 1.1415 0.02035 0.01341 0.0176 0.1218 1.0000 10.000 1.1543 0.02122 0.01429 0.0193 0.1071 1.0000 10.250 1.1651 0.02215 0.01524 0.0213 0.0942 1.0000 10.500 1.1736 0.02315 0.01626 0.0236 0.0832 1.0000 10.750 1.1790 0.02424 0.01737 0.0262 0.0737 1.0000 11.000 1.1828 0.02527 0.01850 0.0291 0.0657 1.0000 11.250 1.1821 0.02639 0.01968 0.0325 0.0597 1.0000 11.500 1.1764 0.02753 0.02088 0.0366 0.0550 1.0000 11.750 1.1586 0.02869 0.02210 0.0422 0.0528 1.0000 12.000 1.1437 0.03026 0.02375 0.0460 0.0507 1.0000 12.250 1.1338 0.03220 0.02578 0.0483 0.0477 1.0000 12.500 1.1238 0.03466 0.02832 0.0496 0.0450 1.0000 12.750 1.1138 0.03753 0.03126 0.0502 0.0427 1.0000 13.000 1.1047 0.04063 0.03444 0.0503 0.0407 1.0000 13.250 1.0982 0.04362 0.03755 0.0502 0.0381 1.0000 13.500 1.0899 0.04697 0.04099 0.0499 0.0360 1.0000 13.750 1.0798 0.05065 0.04473 0.0492 0.0343 1.0000 14.000 1.0671 0.05477 0.04891 0.0483 0.0326 1.0000 14.250 1.0575 0.05860 0.05282 0.0474 0.0315 1.0000 14.500 1.0499 0.06227 0.05662 0.0465 0.0301 1.0000 14.750 1.0422 0.06610 0.06055 0.0454 0.0283 1.0000 15.000 1.0337 0.07020 0.06474 0.0441 0.0272 1.0000 15.250 1.0235 0.07474 0.06935 0.0425 0.0257 1.0000 15.500 1.0132 0.07938 0.07405 0.0407 0.0247 1.0000 15.750 1.0027 0.08413 0.07884 0.0390 0.0238 1.0000 16.000 0.9980 0.08820 0.08305 0.0375 0.0225 1.0000 16.250 0.9913 0.09264 0.08759 0.0357 0.0213 1.0000 16.500 0.9839 0.09732 0.09238 0.0338 0.0201 1.0000 16.750 0.9769 0.10197 0.09711 0.0319 0.0195 1.0000 17.000 0.9675 0.10717 0.10238 0.0296 0.0185 1.0000 17.250 0.9583 0.11239 0.10764 0.0273 0.0178 1.0000