XFOIL Version 6.96 Calculated polar for: EPPLER 584 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.1073 0.09337 0.08816 -0.1068 0.8802 0.0233 -10.500 -0.0971 0.08931 0.08403 -0.1103 0.8685 0.0228 -10.250 -0.0905 0.08490 0.07956 -0.1138 0.8580 0.0222 -10.000 -0.0900 0.07976 0.07439 -0.1175 0.8479 0.0219 -9.500 -0.1225 0.06308 0.05755 -0.1297 0.8290 0.0196 -9.250 -0.1336 0.05933 0.05370 -0.1307 0.8195 0.0194 -9.000 -0.1491 0.05545 0.04964 -0.1307 0.8120 0.0193 -8.750 -0.1646 0.05263 0.04668 -0.1287 0.8040 0.0192 -8.500 -0.1786 0.05009 0.04394 -0.1258 0.7977 0.0190 -8.250 -0.1870 0.04735 0.04094 -0.1232 0.7925 0.0189 -8.000 -0.1927 0.04480 0.03815 -0.1203 0.7867 0.0187 -7.750 -0.1957 0.04193 0.03491 -0.1173 0.7817 0.0187 -7.500 -0.1923 0.03921 0.03177 -0.1148 0.7779 0.0186 -7.250 -0.1876 0.03693 0.02913 -0.1120 0.7729 0.0186 -7.000 -0.1788 0.03463 0.02638 -0.1096 0.7685 0.0190 -6.750 -0.1651 0.03238 0.02357 -0.1075 0.7650 0.0198 -6.500 -0.1452 0.03125 0.02230 -0.1068 0.7621 0.0206 -6.250 -0.1263 0.03012 0.02094 -0.1057 0.7589 0.0222 -6.000 -0.1068 0.02870 0.01916 -0.1043 0.7550 0.0232 -5.750 -0.0846 0.02742 0.01770 -0.1034 0.7514 0.0241 -5.500 -0.0608 0.02637 0.01654 -0.1028 0.7483 0.0252 -5.250 -0.0354 0.02531 0.01531 -0.1024 0.7456 0.0268 -5.000 -0.0131 0.02449 0.01439 -0.1015 0.7428 0.0287 -4.750 0.0051 0.02402 0.01386 -0.1000 0.7392 0.0326 -4.500 0.0239 0.02348 0.01334 -0.0986 0.7357 0.0368 -4.250 0.0440 0.02288 0.01269 -0.0973 0.7325 0.0428 -4.000 0.0658 0.02229 0.01207 -0.0964 0.7298 0.0542 -3.750 0.0884 0.02166 0.01153 -0.0956 0.7275 0.0764 -3.500 0.1022 0.02132 0.01140 -0.0933 0.7235 0.1119 -3.250 0.1182 0.02078 0.01127 -0.0916 0.7199 0.1851 -3.000 0.1315 0.01993 0.01112 -0.0894 0.7166 0.3413 -2.750 0.1773 0.02036 0.01314 -0.0881 0.7149 0.7382 -2.500 0.1744 0.02049 0.01310 -0.0826 0.7122 0.7901 -2.250 0.1799 0.02114 0.01367 -0.0779 0.7079 0.8202 -2.000 0.1996 0.02179 0.01418 -0.0753 0.7042 0.8438 -1.750 0.2323 0.02228 0.01449 -0.0752 0.7014 0.8640 -1.500 0.2900 0.02282 0.01478 -0.0793 0.6995 0.8908 -1.250 0.3738 0.02294 0.01460 -0.0894 0.6979 0.9100 -1.000 0.3994 0.02301 0.01455 -0.0892 0.6950 0.9188 -0.750 0.4301 0.02312 0.01457 -0.0904 0.6910 0.9241 -0.500 0.4476 0.02322 0.01459 -0.0888 0.6875 0.9310 -0.250 0.4814 0.02313 0.01437 -0.0903 0.6848 0.9341 0.000 0.5159 0.02301 0.01411 -0.0920 0.6826 0.9370 0.250 0.5337 0.02322 0.01429 -0.0907 0.6787 0.9417 0.500 0.5477 0.02344 0.01448 -0.0886 0.6745 0.9463 0.750 0.5778 0.02343 0.01439 -0.0895 0.6714 0.9485 1.000 0.6089 0.02337 0.01423 -0.0906 0.6690 0.9507 1.250 0.6353 0.02341 0.01420 -0.0907 0.6663 0.9532 1.500 0.6377 0.02390 0.01475 -0.0866 0.6608 0.9581 1.750 0.6638 0.02398 0.01479 -0.0868 0.6573 0.9599 2.000 0.6955 0.02393 0.01468 -0.0880 0.6547 0.9614 2.250 0.7240 0.02396 0.01466 -0.0885 0.6519 0.9630 2.500 0.7273 0.02461 0.01540 -0.0849 0.6457 0.9668 2.750 0.7482 0.02473 0.01551 -0.0840 0.6421 0.9690 3.000 0.7755 0.02469 0.01542 -0.0841 0.6395 0.9702 3.250 0.7823 0.02535 0.01617 -0.0813 0.6333 0.9733 3.500 0.8006 0.02564 0.01649 -0.0802 0.6286 0.9754 3.750 0.8290 0.02559 0.01643 -0.0806 0.6257 0.9763 4.000 0.8244 0.02647 0.01741 -0.0758 0.6186 0.9805 4.250 0.8386 0.02675 0.01772 -0.0739 0.6137 0.9828 4.500 0.8707 0.02657 0.01754 -0.0748 0.6110 0.9833 4.750 0.8542 0.02787 0.01897 -0.0686 0.6015 0.9881 5.000 0.8827 0.02777 0.01890 -0.0690 0.5981 0.9895 5.500 0.8818 0.02898 0.02025 -0.0611 0.5846 0.9973 5.750 0.8831 0.02952 0.02084 -0.0575 0.5785 1.0000 6.250 0.8067 0.03249 0.02386 -0.0390 0.5580 1.0000 6.500 0.8248 0.03214 0.02353 -0.0373 0.5545 1.0000 6.750 0.8539 0.03141 0.02285 -0.0369 0.5525 1.0000 7.250 0.8527 0.03305 0.02456 -0.0304 0.5372 1.0000 7.500 0.8871 0.03225 0.02379 -0.0308 0.5352 1.0000 8.000 0.8664 0.03664 0.02831 -0.0252 0.5103 1.0000 8.250 0.8969 0.03608 0.02782 -0.0254 0.5071 1.0000 8.500 0.9337 0.03507 0.02688 -0.0259 0.5049 1.0000 9.000 0.9658 0.03620 0.02815 -0.0246 0.4897 1.0000 9.500 1.0018 0.03711 0.02922 -0.0237 0.4743 1.0000 10.000 1.0417 0.03774 0.03001 -0.0230 0.4585 1.0000 10.250 1.0436 0.03959 0.03195 -0.0218 0.4463 1.0000 10.500 1.0755 0.03888 0.03132 -0.0220 0.4400 1.0000 10.750 1.0866 0.03997 0.03249 -0.0213 0.4289 1.0000 11.000 1.0979 0.04108 0.03369 -0.0206 0.4180 1.0000 11.250 1.1347 0.03990 0.03255 -0.0209 0.4101 1.0000 11.500 1.1379 0.04169 0.03443 -0.0199 0.3970 1.0000 11.750 1.1476 0.04296 0.03577 -0.0192 0.3846 1.0000 12.000 1.1630 0.04370 0.03657 -0.0187 0.3725 1.0000 12.250 1.1798 0.04429 0.03720 -0.0182 0.3601 1.0000 12.500 1.1947 0.04506 0.03799 -0.0176 0.3470 1.0000 12.750 1.1999 0.04680 0.03979 -0.0169 0.3332 1.0000 13.000 1.2062 0.04848 0.04152 -0.0162 0.3196 1.0000 13.250 1.2126 0.05017 0.04326 -0.0156 0.3058 1.0000 13.500 1.2187 0.05191 0.04503 -0.0150 0.2922 1.0000 13.750 1.2241 0.05377 0.04691 -0.0145 0.2786 1.0000 14.000 1.2288 0.05573 0.04889 -0.0140 0.2650 1.0000 14.250 1.2321 0.05787 0.05104 -0.0135 0.2515 1.0000 14.500 1.2346 0.06018 0.05336 -0.0132 0.2385 1.0000 14.750 1.2346 0.06286 0.05611 -0.0130 0.2254 1.0000 15.000 1.2348 0.06561 0.05891 -0.0128 0.2128 1.0000 15.250 1.2346 0.06843 0.06177 -0.0128 0.2005 1.0000 15.500 1.2340 0.07136 0.06473 -0.0129 0.1887 1.0000 15.750 1.2324 0.07449 0.06786 -0.0130 0.1770 1.0000 16.000 1.2302 0.07781 0.07124 -0.0134 0.1657 1.0000 16.250 1.2278 0.08124 0.07474 -0.0139 0.1548 1.0000 16.500 1.2248 0.08481 0.07836 -0.0145 0.1445 1.0000 16.750 1.2211 0.08850 0.08205 -0.0152 0.1350 1.0000 17.000 1.2175 0.09234 0.08599 -0.0161 0.1254 1.0000 17.250 1.2140 0.09620 0.08991 -0.0170 0.1166 1.0000 17.500 1.2088 0.10032 0.09402 -0.0182 0.1086 1.0000 17.750 1.2051 0.10438 0.09820 -0.0195 0.1006 1.0000 18.000 1.2007 0.10853 0.10240 -0.0209 0.0935 1.0000 18.250 1.1958 0.11285 0.10678 -0.0224 0.0869 1.0000 18.500 1.1924 0.11699 0.11100 -0.0240 0.0806 1.0000