XFOIL Version 6.96 Calculated polar for: EPPLER 1213 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.9353 0.08553 0.08091 -0.0250 1.0000 0.0210 -16.000 -0.9484 0.08017 0.07548 -0.0277 1.0000 0.0211 -15.750 -0.9656 0.07445 0.06968 -0.0306 1.0000 0.0212 -15.500 -0.9884 0.06824 0.06337 -0.0338 1.0000 0.0213 -15.250 -1.0116 0.06207 0.05709 -0.0369 1.0000 0.0213 -15.000 -1.0390 0.05536 0.05025 -0.0403 1.0000 0.0213 -14.750 -1.0664 0.04855 0.04330 -0.0439 1.0000 0.0214 -14.500 -1.0881 0.04223 0.03683 -0.0475 1.0000 0.0213 -14.250 -1.1057 0.03636 0.03079 -0.0512 1.0000 0.0214 -14.000 -1.1180 0.03178 0.02607 -0.0540 1.0000 0.0217 -13.750 -1.1251 0.02874 0.02291 -0.0547 1.0000 0.0219 -13.500 -1.1281 0.02671 0.02078 -0.0539 1.0000 0.0222 -13.250 -1.1284 0.02523 0.01923 -0.0521 1.0000 0.0226 -13.000 -1.1256 0.02413 0.01806 -0.0498 1.0000 0.0229 -12.750 -1.1216 0.02322 0.01709 -0.0470 1.0000 0.0235 -12.500 -1.1138 0.02239 0.01620 -0.0445 1.0000 0.0241 -12.250 -1.1027 0.02153 0.01531 -0.0425 1.0000 0.0249 -12.000 -1.0891 0.02077 0.01451 -0.0408 1.0000 0.0260 -11.750 -1.0735 0.02008 0.01379 -0.0391 1.0000 0.0273 -11.500 -1.0583 0.01933 0.01302 -0.0375 1.0000 0.0296 -11.250 -1.0420 0.01863 0.01232 -0.0359 1.0000 0.0325 -11.000 -1.0257 0.01791 0.01161 -0.0342 1.0000 0.0376 -10.750 -1.0059 0.01720 0.01092 -0.0332 0.9975 0.0444 -10.500 -0.9697 0.01629 0.01006 -0.0356 0.9525 0.0555 -10.250 -0.9247 0.01547 0.00918 -0.0395 0.8808 0.0690 -10.000 -0.9049 0.01504 0.00863 -0.0380 0.8324 0.0788 -9.750 -0.8841 0.01465 0.00816 -0.0367 0.7999 0.0882 -9.500 -0.8619 0.01429 0.00773 -0.0357 0.7738 0.0974 -9.250 -0.8386 0.01398 0.00736 -0.0348 0.7511 0.1056 -9.000 -0.8145 0.01370 0.00701 -0.0340 0.7306 0.1135 -8.750 -0.7901 0.01342 0.00669 -0.0332 0.7121 0.1213 -8.500 -0.7651 0.01316 0.00639 -0.0325 0.6948 0.1294 -8.250 -0.7395 0.01296 0.00612 -0.0320 0.6789 0.1373 -8.000 -0.7140 0.01273 0.00587 -0.0314 0.6637 0.1452 -7.750 -0.6876 0.01256 0.00565 -0.0309 0.6487 0.1517 -7.500 -0.6613 0.01239 0.00544 -0.0304 0.6351 0.1583 -7.250 -0.6343 0.01227 0.00525 -0.0299 0.6217 0.1640 -7.000 -0.6077 0.01211 0.00507 -0.0295 0.6087 0.1698 -6.750 -0.5804 0.01200 0.00490 -0.0291 0.5967 0.1757 -6.500 -0.5533 0.01189 0.00474 -0.0287 0.5844 0.1810 -6.250 -0.5259 0.01178 0.00460 -0.0284 0.5729 0.1867 -6.000 -0.4982 0.01172 0.00446 -0.0280 0.5620 0.1913 -5.750 -0.4708 0.01161 0.00432 -0.0277 0.5504 0.1954 -5.500 -0.4432 0.01151 0.00418 -0.0273 0.5404 0.1992 -5.250 -0.4155 0.01144 0.00406 -0.0270 0.5298 0.2029 -5.000 -0.3875 0.01138 0.00393 -0.0267 0.5198 0.2061 -4.750 -0.3596 0.01132 0.00380 -0.0264 0.5096 0.2089 -4.500 -0.3319 0.01122 0.00369 -0.0261 0.5008 0.2126 -4.250 -0.3041 0.01116 0.00358 -0.0258 0.4908 0.2160 -4.000 -0.2760 0.01111 0.00349 -0.0255 0.4819 0.2193 -3.750 -0.2478 0.01107 0.00339 -0.0253 0.4729 0.2224 -3.500 -0.2198 0.01103 0.00330 -0.0250 0.4645 0.2253 -3.250 -0.1919 0.01096 0.00321 -0.0247 0.4553 0.2286 -3.000 -0.1640 0.01092 0.00313 -0.0244 0.4472 0.2321 -2.750 -0.1357 0.01088 0.00307 -0.0242 0.4393 0.2358 -2.250 -0.0792 0.01085 0.00294 -0.0237 0.4230 0.2414 -2.000 -0.0514 0.01080 0.00288 -0.0234 0.4151 0.2454 -1.750 -0.0234 0.01078 0.00285 -0.0232 0.4083 0.2494 -1.500 0.0049 0.01076 0.00281 -0.0230 0.4004 0.2531 -1.250 0.0329 0.01078 0.00277 -0.0227 0.3928 0.2565 -1.000 0.0613 0.01077 0.00275 -0.0225 0.3860 0.2601 -0.750 0.0891 0.01075 0.00272 -0.0223 0.3787 0.2647 -0.500 0.1172 0.01075 0.00272 -0.0220 0.3718 0.2691 -0.250 0.1454 0.01076 0.00271 -0.0218 0.3647 0.2734 0.000 0.1733 0.01081 0.00271 -0.0216 0.3577 0.2777 0.250 0.2013 0.01079 0.00271 -0.0213 0.3513 0.2836 0.500 0.2293 0.01081 0.00273 -0.0211 0.3442 0.2894 0.750 0.2572 0.01086 0.00275 -0.0209 0.3378 0.2947 1.000 0.2852 0.01086 0.00278 -0.0206 0.3314 0.3010 1.250 0.3129 0.01090 0.00281 -0.0204 0.3249 0.3089 1.500 0.3406 0.01094 0.00286 -0.0201 0.3197 0.3170 1.750 0.3685 0.01095 0.00291 -0.0199 0.3140 0.3269 2.000 0.3961 0.01101 0.00296 -0.0196 0.3077 0.3362 2.250 0.4235 0.01105 0.00303 -0.0194 0.3022 0.3480 2.500 0.4512 0.01108 0.00310 -0.0191 0.2969 0.3606 2.750 0.4785 0.01113 0.00318 -0.0188 0.2916 0.3760 3.000 0.5055 0.01119 0.00328 -0.0185 0.2867 0.3949 3.250 0.5329 0.01120 0.00337 -0.0182 0.2821 0.4158 3.500 0.5599 0.01123 0.00347 -0.0179 0.2766 0.4386 3.750 0.5863 0.01130 0.00359 -0.0175 0.2711 0.4647 4.250 0.6396 0.01132 0.00384 -0.0168 0.2624 0.5321 4.500 0.6653 0.01134 0.00398 -0.0162 0.2578 0.5759 4.750 0.6903 0.01136 0.00414 -0.0156 0.2536 0.6247 5.000 0.7156 0.01133 0.00430 -0.0149 0.2497 0.6771 5.250 0.7397 0.01130 0.00446 -0.0140 0.2452 0.7364 5.500 0.7620 0.01126 0.00464 -0.0127 0.2406 0.8101 5.750 0.7933 0.01125 0.00490 -0.0130 0.2364 0.9104 6.000 0.8522 0.01148 0.00516 -0.0192 0.2312 0.9695 6.250 0.8886 0.01171 0.00537 -0.0210 0.2266 0.9862 6.500 0.9236 0.01199 0.00560 -0.0225 0.2224 0.9965 6.750 0.9546 0.01218 0.00580 -0.0231 0.2190 1.0000 7.000 0.9778 0.01239 0.00600 -0.0222 0.2153 1.0000 7.250 1.0005 0.01263 0.00622 -0.0211 0.2115 1.0000 7.500 1.0226 0.01291 0.00647 -0.0201 0.2081 1.0000 7.750 1.0455 0.01313 0.00670 -0.0191 0.2055 1.0000 8.000 1.0685 0.01335 0.00694 -0.0182 0.2028 1.0000 8.250 1.0911 0.01360 0.00719 -0.0172 0.1999 1.0000 8.500 1.1131 0.01388 0.00747 -0.0161 0.1969 1.0000 8.750 1.1344 0.01421 0.00777 -0.0150 0.1939 1.0000 9.000 1.1563 0.01449 0.00807 -0.0140 0.1914 1.0000 9.250 1.1786 0.01475 0.00836 -0.0131 0.1889 1.0000 9.500 1.2003 0.01504 0.00867 -0.0120 0.1865 1.0000 9.750 1.2212 0.01537 0.00900 -0.0109 0.1841 1.0000 10.000 1.2411 0.01573 0.00937 -0.0097 0.1817 1.0000 10.250 1.2597 0.01614 0.00977 -0.0084 0.1792 1.0000 10.500 1.2795 0.01647 0.01014 -0.0071 0.1772 1.0000 10.750 1.2990 0.01680 0.01052 -0.0059 0.1753 1.0000 11.000 1.3170 0.01717 0.01092 -0.0045 0.1733 1.0000 11.250 1.3317 0.01757 0.01135 -0.0025 0.1713 1.0000 11.500 1.3442 0.01804 0.01184 -0.0003 0.1691 1.0000 11.750 1.3555 0.01859 0.01240 0.0019 0.1670 1.0000 12.000 1.3654 0.01925 0.01307 0.0040 0.1649 1.0000 12.250 1.3801 0.01977 0.01366 0.0055 0.1634 1.0000 12.500 1.3935 0.02040 0.01435 0.0069 0.1617 1.0000 12.750 1.4056 0.02115 0.01515 0.0082 0.1596 1.0000 13.000 1.4164 0.02203 0.01608 0.0094 0.1577 1.0000 13.250 1.4256 0.02309 0.01717 0.0105 0.1555 1.0000 13.500 1.4332 0.02436 0.01847 0.0115 0.1535 1.0000 13.750 1.4406 0.02573 0.01988 0.0123 0.1516 1.0000 14.000 1.4522 0.02687 0.02110 0.0128 0.1499 1.0000 14.250 1.4621 0.02819 0.02249 0.0132 0.1480 1.0000 14.500 1.4699 0.02973 0.02409 0.0135 0.1458 1.0000 14.750 1.4753 0.03152 0.02593 0.0138 0.1435 1.0000 15.000 1.4785 0.03357 0.02803 0.0139 0.1415 1.0000 15.250 1.4796 0.03586 0.03035 0.0139 0.1395 1.0000 15.500 1.4862 0.03768 0.03226 0.0139 0.1377 1.0000 15.750 1.4906 0.03974 0.03440 0.0138 0.1358 1.0000 16.000 1.4920 0.04213 0.03686 0.0136 0.1334 1.0000 16.250 1.4897 0.04494 0.03972 0.0132 0.1310 1.0000 16.500 1.4856 0.04798 0.04281 0.0127 0.1290 1.0000 16.750 1.4827 0.05098 0.04588 0.0121 0.1267 1.0000 17.000 1.4824 0.05379 0.04878 0.0115 0.1245 1.0000 17.250 1.4783 0.05710 0.05216 0.0106 0.1217 1.0000 17.500 1.4723 0.06068 0.05580 0.0096 0.1197 1.0000 17.750 1.4599 0.06516 0.06032 0.0082 0.1167 1.0000 18.000 1.4578 0.06838 0.06363 0.0072 0.1144 1.0000 18.250 1.4515 0.07220 0.06753 0.0060 0.1120 1.0000 18.500 1.4413 0.07663 0.07202 0.0044 0.1093 1.0000 18.750 1.4258 0.08181 0.07724 0.0024 0.1065 1.0000 19.000 1.4184 0.08599 0.08151 0.0009 0.1034 1.0000 19.250 1.4085 0.09058 0.08616 -0.0009 0.1007 1.0000