XFOIL Version 6.96 Calculated polar for: EPPLER 638 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.2357 0.11093 0.10665 -0.0231 1.0000 0.0445 -10.250 -0.2421 0.10817 0.10395 -0.0258 1.0000 0.0451 -10.000 -0.2468 0.10513 0.10096 -0.0283 1.0000 0.0453 -9.750 -0.2495 0.10182 0.09772 -0.0304 1.0000 0.0454 -9.500 -0.2284 0.09652 0.09247 -0.0274 1.0000 0.0470 -9.250 -0.2219 0.09312 0.08913 -0.0275 1.0000 0.0481 -9.000 -0.2184 0.08973 0.08581 -0.0281 1.0000 0.0494 -8.750 -0.2101 0.08548 0.08157 -0.0310 0.9267 0.0507 -8.500 -0.3055 0.09167 0.08747 -0.0299 1.0000 0.0469 -8.250 -0.2998 0.08860 0.08447 -0.0297 1.0000 0.0480 -8.000 -0.2992 0.08556 0.08154 -0.0306 1.0000 0.0489 -7.750 -0.2783 0.08033 0.07624 -0.0389 0.8972 0.0507 -7.500 -0.2639 0.07568 0.07139 -0.0454 0.8427 0.0523 -7.000 -0.2664 0.06988 0.06489 -0.0522 0.7810 0.0565 -6.750 -0.2615 0.06730 0.06198 -0.0521 0.7602 0.0567 -6.500 -0.2512 0.06174 0.05647 -0.0519 0.7421 0.0576 -6.000 -0.2269 0.05230 0.04659 -0.0505 0.7125 0.0347 -5.500 -0.2035 0.04513 0.03883 -0.0484 0.6862 0.0306 -5.250 -0.1881 0.04249 0.03590 -0.0473 0.6735 0.0311 -5.000 -0.1713 0.04004 0.03313 -0.0461 0.6617 0.0325 -4.750 -0.1540 0.03731 0.03000 -0.0446 0.6513 0.0325 -4.500 -0.1355 0.03452 0.02678 -0.0430 0.6403 0.0317 -4.250 -0.1155 0.03197 0.02376 -0.0413 0.6302 0.0313 -4.000 -0.0941 0.02982 0.02114 -0.0398 0.6209 0.0314 -3.750 -0.0711 0.02811 0.01905 -0.0385 0.6105 0.0327 -3.500 -0.0468 0.02660 0.01706 -0.0373 0.6013 0.0349 -3.250 -0.0212 0.02510 0.01511 -0.0362 0.5920 0.0359 -3.000 0.0050 0.02366 0.01338 -0.0355 0.5829 0.0367 -2.750 0.0307 0.02265 0.01223 -0.0350 0.5748 0.0389 -2.500 0.0571 0.02188 0.01134 -0.0344 0.5658 0.0422 -2.250 0.0839 0.02101 0.01025 -0.0338 0.5585 0.0438 -2.000 0.1101 0.02029 0.00941 -0.0331 0.5498 0.0456 -1.750 0.1344 0.01963 0.00874 -0.0324 0.5432 0.0496 -1.500 0.1587 0.01916 0.00822 -0.0315 0.5353 0.0532 -1.250 0.1830 0.01878 0.00766 -0.0305 0.5290 0.0564 -1.000 0.2071 0.01840 0.00724 -0.0297 0.5219 0.0621 -0.750 0.2322 0.01812 0.00688 -0.0290 0.5154 0.0739 -0.500 0.4049 0.01568 0.00682 -0.0560 0.5020 1.0000 -0.250 0.4277 0.01576 0.00666 -0.0551 0.4970 1.0000 0.000 0.4506 0.01586 0.00663 -0.0543 0.4905 1.0000 0.250 0.4734 0.01596 0.00656 -0.0534 0.4850 1.0000 0.500 0.4963 0.01610 0.00652 -0.0526 0.4802 1.0000 0.750 0.5191 0.01624 0.00658 -0.0518 0.4746 1.0000 1.000 0.5420 0.01639 0.00660 -0.0509 0.4698 1.0000 1.250 0.5649 0.01657 0.00664 -0.0500 0.4654 1.0000 1.500 0.5875 0.01675 0.00678 -0.0492 0.4599 1.0000 1.750 0.6103 0.01694 0.00687 -0.0484 0.4554 1.0000 2.000 0.6334 0.01714 0.00694 -0.0475 0.4518 1.0000 2.250 0.6558 0.01738 0.00719 -0.0467 0.4469 1.0000 2.500 0.6783 0.01760 0.00737 -0.0458 0.4422 1.0000 2.750 0.7012 0.01782 0.00750 -0.0450 0.4383 1.0000 3.000 0.7238 0.01808 0.00772 -0.0441 0.4345 1.0000 3.250 0.7459 0.01838 0.00805 -0.0432 0.4300 1.0000 3.500 0.7683 0.01864 0.00828 -0.0424 0.4259 1.0000 3.750 0.7913 0.01889 0.00846 -0.0415 0.4225 1.0000 4.000 0.8132 0.01922 0.00882 -0.0406 0.4185 1.0000 4.250 0.8347 0.01956 0.00921 -0.0397 0.4142 1.0000 4.500 0.8570 0.01987 0.00952 -0.0388 0.4106 1.0000 4.750 0.8800 0.02015 0.00978 -0.0380 0.4074 1.0000 5.000 0.9012 0.02053 0.01021 -0.0371 0.4035 1.0000 5.250 0.9220 0.02093 0.01070 -0.0360 0.3992 1.0000 5.500 0.9438 0.02129 0.01108 -0.0351 0.3957 1.0000 5.750 0.9667 0.02160 0.01139 -0.0344 0.3926 1.0000 6.000 0.9874 0.02203 0.01190 -0.0334 0.3889 1.0000 6.250 1.0069 0.02252 0.01251 -0.0322 0.3846 1.0000 6.500 1.0280 0.02292 0.01297 -0.0313 0.3810 1.0000 6.750 1.0507 0.02325 0.01333 -0.0305 0.3779 1.0000 7.000 1.0709 0.02373 0.01389 -0.0295 0.3743 1.0000 7.250 1.0886 0.02430 0.01463 -0.0281 0.3697 1.0000 7.500 1.1088 0.02473 0.01517 -0.0271 0.3660 1.0000 7.750 1.1316 0.02505 0.01549 -0.0263 0.3627 1.0000 8.000 1.1490 0.02563 0.01623 -0.0250 0.3585 1.0000 8.250 1.1653 0.02623 0.01700 -0.0235 0.3537 1.0000 8.500 1.1859 0.02658 0.01743 -0.0225 0.3497 1.0000 8.750 1.2084 0.02688 0.01775 -0.0218 0.3461 1.0000 9.000 1.2192 0.02771 0.01884 -0.0197 0.3405 1.0000 9.250 1.2373 0.02812 0.01936 -0.0184 0.3358 1.0000 9.500 1.2617 0.02823 0.01948 -0.0179 0.3320 1.0000 9.750 1.2677 0.02921 0.02076 -0.0153 0.3258 1.0000 10.000 1.2846 0.02957 0.02122 -0.0139 0.3207 1.0000 10.250 1.3019 0.02993 0.02166 -0.0125 0.3157 1.0000 10.500 1.3073 0.03083 0.02279 -0.0099 0.3094 1.0000 10.750 1.3260 0.03098 0.02301 -0.0087 0.3042 1.0000 11.000 1.3274 0.03200 0.02425 -0.0058 0.2981 1.0000 11.250 1.3338 0.03261 0.02498 -0.0032 0.2921 1.0000 11.500 1.3385 0.03328 0.02575 -0.0006 0.2866 1.0000 11.750 1.3304 0.03475 0.02740 0.0027 0.2803 1.0000 12.000 1.3406 0.03522 0.02791 0.0044 0.2742 1.0000 12.250 1.3211 0.03802 0.03093 0.0067 0.2676 1.0000 12.500 1.3300 0.03880 0.03176 0.0078 0.2608 1.0000 12.750 1.3011 0.04336 0.03652 0.0084 0.2540 1.0000 13.000 1.3081 0.04459 0.03779 0.0090 0.2468 1.0000 13.250 1.2684 0.05136 0.04475 0.0080 0.2394 1.0000 13.500 1.2698 0.05350 0.04693 0.0080 0.2319 1.0000 13.750 1.2318 0.06091 0.05445 0.0062 0.2238 1.0000 14.000 1.2208 0.06495 0.05855 0.0054 0.2158 1.0000 14.250 1.2177 0.06792 0.06157 0.0049 0.2074 1.0000 14.500 1.1895 0.07477 0.06849 0.0029 0.1987 1.0000 14.750 1.1971 0.07634 0.07008 0.0029 0.1907 1.0000 15.000 1.1844 0.08117 0.07498 0.0015 0.1820 1.0000 15.250 1.1754 0.08551 0.07938 0.0003 0.1735 1.0000 15.500 1.1845 0.08692 0.08076 0.0002 0.1652 1.0000 15.750 1.1710 0.09220 0.08612 -0.0015 0.1570 1.0000 16.000 1.1701 0.09541 0.08936 -0.0024 0.1492 1.0000 16.250 1.1712 0.09826 0.09220 -0.0032 0.1413 1.0000 16.500 1.1609 0.10326 0.09728 -0.0050 0.1340 1.0000 16.750 1.1660 0.10545 0.09943 -0.0056 0.1267 1.0000 17.000 1.1541 0.11095 0.10507 -0.0077 0.1200 1.0000 17.250 1.1559 0.11382 0.10790 -0.0087 0.1133 1.0000