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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5438 0.08533 0.08387 0.0016 1.0000 0.0072 -8.750 -0.5559 0.07978 0.07832 -0.0033 1.0000 0.0072 -8.500 -0.5695 0.07542 0.07395 -0.0049 1.0000 0.0070 -8.250 -0.5837 0.07173 0.07022 -0.0042 1.0000 0.0070 -8.000 -0.5949 0.06817 0.06661 -0.0026 1.0000 0.0070 -7.750 -0.5996 0.06387 0.06222 -0.0015 1.0000 0.0073 -7.500 -0.6001 0.05983 0.05809 -0.0002 1.0000 0.0074 -6.750 -0.5745 0.04823 0.04548 0.0044 0.7786 0.0078 -6.500 -0.5660 0.04476 0.04175 0.0068 0.7522 0.0078 -6.250 -0.5569 0.04116 0.03788 0.0095 0.7296 0.0078 -6.000 -0.5473 0.03758 0.03400 0.0124 0.7113 0.0078 -5.750 -0.5532 0.03108 0.02703 0.0172 0.6971 0.0083 -5.500 -0.5376 0.02936 0.02512 0.0189 0.6796 0.0085 -5.250 -0.5202 0.02768 0.02324 0.0206 0.6632 0.0087 -5.000 -0.5018 0.02596 0.02129 0.0223 0.6473 0.0090 -4.750 -0.4821 0.02415 0.01924 0.0240 0.6324 0.0094 -4.500 -0.4608 0.02238 0.01719 0.0257 0.6185 0.0101 -4.250 -0.4340 0.02224 0.01682 0.0269 0.6043 0.0114 -4.000 -0.4113 0.02133 0.01562 0.0283 0.5910 0.0115 -3.750 -0.3880 0.01519 0.00889 0.0306 0.5808 0.0085 -3.500 -0.3602 0.01254 0.00590 0.0319 0.5691 0.0054 -3.250 -0.3353 0.01187 0.00513 0.0327 0.5573 0.0054 -3.000 -0.3112 0.01127 0.00443 0.0336 0.5452 0.0054 -2.750 -0.2881 0.01063 0.00368 0.0348 0.5340 0.0057 -2.500 -0.2633 0.01027 0.00326 0.0356 0.5227 0.0062 -2.250 -0.2379 0.01002 0.00295 0.0362 0.5121 0.0071 -2.000 -0.2123 0.00980 0.00266 0.0368 0.5015 0.0076 -1.750 -0.1871 0.00953 0.00232 0.0375 0.4911 0.0097 -1.500 -0.1615 0.00931 0.00208 0.0381 0.4817 0.0150 -1.250 -0.1392 0.00882 0.00187 0.0392 0.4729 0.0940 -1.000 -0.1149 0.00854 0.00178 0.0399 0.4635 0.1639 -0.750 -0.1034 0.00735 0.00153 0.0428 0.4563 0.4404 -0.500 -0.1115 0.00571 0.00123 0.0503 0.4507 0.7911 -0.250 -0.0919 0.00577 0.00158 0.0528 0.4433 0.9018 0.000 -0.0651 0.00601 0.00179 0.0536 0.4350 0.9177 0.250 -0.0389 0.00633 0.00206 0.0544 0.4274 0.9300 0.500 -0.0018 0.00668 0.00235 0.0529 0.4190 0.9349 0.750 0.0310 0.00694 0.00255 0.0521 0.4118 0.9392 1.000 0.0577 0.00715 0.00269 0.0526 0.4043 0.9446 1.250 0.0938 0.00731 0.00280 0.0510 0.3972 0.9458 1.500 0.1296 0.00747 0.00289 0.0493 0.3900 0.9467 1.750 0.1650 0.00760 0.00297 0.0477 0.3833 0.9475 2.000 0.1986 0.00770 0.00302 0.0465 0.3764 0.9482 2.250 0.2324 0.00780 0.00307 0.0452 0.3702 0.9489 2.500 0.2644 0.00787 0.00311 0.0442 0.3639 0.9498 2.750 0.2949 0.00796 0.00315 0.0436 0.3578 0.9508 3.000 0.3247 0.00800 0.00318 0.0431 0.3523 0.9520 3.250 0.3509 0.00808 0.00322 0.0434 0.3463 0.9537 3.500 0.3563 0.00806 0.00321 0.0483 0.3425 0.9585 3.750 0.3930 0.00815 0.00328 0.0463 0.3361 0.9590 4.000 0.4250 0.00824 0.00333 0.0452 0.3298 0.9593 4.250 0.4596 0.00830 0.00339 0.0437 0.3242 0.9598 4.500 0.4936 0.00841 0.00348 0.0422 0.3177 0.9603 4.750 0.5271 0.00850 0.00356 0.0409 0.3120 0.9609 5.000 0.5600 0.00859 0.00365 0.0396 0.3056 0.9616 5.250 0.5931 0.00871 0.00376 0.0383 0.2992 0.9625 5.500 0.6223 0.00878 0.00383 0.0379 0.2929 0.9632 5.750 0.6500 0.00887 0.00391 0.0377 0.2861 0.9639 6.000 0.6773 0.00893 0.00399 0.0376 0.2793 0.9647 6.250 0.7035 0.00904 0.00409 0.0377 0.2724 0.9657 6.500 0.7294 0.00912 0.00418 0.0380 0.2655 0.9667 6.750 0.7537 0.00925 0.00430 0.0385 0.2577 0.9682 7.000 0.7726 0.00933 0.00441 0.0402 0.2512 0.9701 7.250 0.7862 0.00945 0.00452 0.0430 0.2440 0.9724 7.500 0.8154 0.00957 0.00464 0.0424 0.2344 0.9727 7.750 0.8445 0.00971 0.00479 0.0418 0.2247 0.9731 8.000 0.8731 0.00991 0.00497 0.0413 0.2125 0.9736 8.250 0.9013 0.01013 0.00518 0.0408 0.2002 0.9741 8.500 0.9297 0.01039 0.00541 0.0402 0.1874 0.9747 8.750 0.9575 0.01069 0.00568 0.0397 0.1726 0.9753 9.000 0.9833 0.01112 0.00603 0.0395 0.1525 0.9761 9.250 1.0084 0.01154 0.00639 0.0394 0.1355 0.9770 9.500 1.0324 0.01200 0.00681 0.0395 0.1180 0.9781 9.750 1.0554 0.01250 0.00725 0.0398 0.1027 0.9793 10.000 1.0758 0.01308 0.00775 0.0405 0.0864 0.9809 10.250 1.0933 0.01358 0.00823 0.0419 0.0752 0.9830 10.500 1.1093 0.01415 0.00875 0.0434 0.0628 0.9850 10.750 1.1354 0.01480 0.00937 0.0427 0.0509 0.9857 11.000 1.1604 0.01555 0.01007 0.0420 0.0390 0.9865 11.250 1.1842 0.01630 0.01080 0.0415 0.0307 0.9875 11.500 1.2065 0.01710 0.01158 0.0413 0.0239 0.9887 11.750 1.2295 0.01772 0.01225 0.0410 0.0211 0.9899 12.000 1.2491 0.01857 0.01311 0.0411 0.0170 0.9917 12.250 1.2683 0.01932 0.01391 0.0414 0.0149 0.9936 12.500 1.2861 0.02036 0.01497 0.0414 0.0119 0.9953 12.750 1.3083 0.02126 0.01595 0.0405 0.0106 0.9966 13.000 1.3234 0.02239 0.01713 0.0404 0.0091 0.9988 13.250 1.3231 0.02366 0.01848 0.0423 0.0080 1.0000 13.500 1.3024 0.02502 0.01993 0.0474 0.0079 1.0000 13.750 1.2896 0.02675 0.02173 0.0506 0.0076 1.0000 14.000 1.2812 0.02896 0.02403 0.0521 0.0072 1.0000 14.250 1.2754 0.03151 0.02665 0.0527 0.0066 1.0000 14.500 1.2685 0.03451 0.02972 0.0526 0.0061 1.0000 14.750 1.2604 0.03787 0.03315 0.0522 0.0052 1.0000 15.000 1.2529 0.04131 0.03670 0.0515 0.0053 1.0000 15.250 1.2451 0.04486 0.04033 0.0507 0.0044 1.0000 15.500 1.2385 0.04835 0.04390 0.0499 0.0045 1.0000 15.750 1.2298 0.05212 0.04777 0.0488 0.0044 1.0000 16.000 1.2138 0.05690 0.05264 0.0474 0.0039 1.0000 16.250 1.1996 0.06161 0.05744 0.0458 0.0036 1.0000 16.500 1.1894 0.06598 0.06188 0.0443 0.0031 1.0000 16.750 1.1769 0.07079 0.06680 0.0425 0.0032 1.0000 17.000 1.1675 0.07529 0.07138 0.0408 0.0028 1.0000 17.250 1.1572 0.07998 0.07616 0.0390 0.0029 1.0000 17.500 1.1437 0.08525 0.08153 0.0369 0.0028 1.0000 17.750 1.1306 0.09058 0.08693 0.0348 0.0024 1.0000 18.000 1.1212 0.09535 0.09180 0.0329 0.0027 1.0000 18.250 1.1057 0.10122 0.09773 0.0304 0.0022 1.0000 18.500 1.0881 0.10760 0.10420 0.0276 0.0019 1.0000 18.750 1.0893 0.11078 0.10746 0.0263 0.0023 1.0000 19.000 1.0697 0.11769 0.11446 0.0233 0.0021 1.0000 19.250 1.0612 0.12272 0.11957 0.0210 0.0021 1.0000