XFOIL Version 6.96 Calculated polar for: EPPLER 361 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4155 0.08619 0.08409 -0.0220 1.0000 0.0219 -10.000 -0.4223 0.08046 0.07837 -0.0245 1.0000 0.0220 -9.750 -0.4327 0.07401 0.07195 -0.0276 1.0000 0.0222 -9.500 -0.4521 0.06529 0.06324 -0.0331 1.0000 0.0222 -9.250 -0.4945 0.05459 0.05244 -0.0408 1.0000 0.0216 -9.000 -0.5249 0.04925 0.04700 -0.0417 1.0000 0.0215 -8.750 -0.5483 0.04562 0.04327 -0.0397 1.0000 0.0216 -8.500 -0.5658 0.04238 0.03993 -0.0367 1.0000 0.0217 -8.250 -0.5750 0.03885 0.03628 -0.0343 1.0000 0.0220 -8.000 -0.5804 0.03539 0.03267 -0.0317 1.0000 0.0224 -7.750 -0.6033 0.03181 0.02841 -0.0250 1.0000 0.0244 -7.500 -0.6399 0.04193 0.03802 -0.0188 1.0000 0.0244 -7.000 -0.6077 0.02369 0.01823 -0.0176 0.9738 0.0132 -6.750 -0.5741 0.02086 0.01522 -0.0193 0.9575 0.0126 -6.500 -0.5381 0.01860 0.01270 -0.0212 0.9353 0.0122 -6.250 -0.5068 0.01705 0.01089 -0.0217 0.9074 0.0120 -6.000 -0.4831 0.01595 0.00955 -0.0206 0.8794 0.0121 -5.750 -0.4609 0.01515 0.00858 -0.0193 0.8555 0.0122 -5.500 -0.4390 0.01447 0.00775 -0.0180 0.8351 0.0123 -5.250 -0.4168 0.01389 0.00703 -0.0168 0.8172 0.0127 -5.000 -0.3947 0.01332 0.00633 -0.0155 0.8010 0.0132 -4.750 -0.3736 0.01265 0.00561 -0.0142 0.7864 0.0142 -4.500 -0.3501 0.01225 0.00514 -0.0132 0.7731 0.0155 -4.250 -0.3272 0.01179 0.00460 -0.0122 0.7610 0.0176 -4.000 -0.3034 0.01142 0.00416 -0.0113 0.7498 0.0211 -3.750 -0.2796 0.01102 0.00377 -0.0104 0.7388 0.0305 -3.500 -0.2565 0.01056 0.00343 -0.0095 0.7292 0.0580 -3.250 -0.2333 0.01016 0.00316 -0.0086 0.7199 0.0986 -3.000 -0.2118 0.00956 0.00290 -0.0076 0.7109 0.1836 -2.750 -0.1948 0.00865 0.00260 -0.0059 0.7030 0.3499 -2.500 -0.1832 0.00750 0.00235 -0.0031 0.6950 0.5724 -2.250 -0.1646 0.00709 0.00233 -0.0009 0.6877 0.6906 -2.000 -0.1407 0.00699 0.00235 0.0002 0.6805 0.7430 -1.750 -0.1152 0.00698 0.00236 0.0010 0.6735 0.7737 -1.500 -0.0890 0.00702 0.00235 0.0017 0.6671 0.7949 -1.250 -0.0625 0.00703 0.00236 0.0022 0.6603 0.8126 -1.000 -0.0361 0.00709 0.00237 0.0028 0.6544 0.8282 -0.750 -0.0103 0.00714 0.00243 0.0036 0.6482 0.8469 -0.500 0.0154 0.00721 0.00249 0.0044 0.6422 0.8629 -0.250 0.0417 0.00731 0.00256 0.0051 0.6368 0.8756 0.000 0.0688 0.00734 0.00261 0.0056 0.6307 0.8856 0.250 0.0948 0.00740 0.00262 0.0062 0.6250 0.8954 0.500 0.1229 0.00747 0.00267 0.0065 0.6191 0.9023 0.750 0.1492 0.00749 0.00267 0.0069 0.6120 0.9101 1.000 0.1777 0.00755 0.00267 0.0070 0.6044 0.9150 1.250 0.2059 0.00756 0.00268 0.0071 0.5953 0.9204 1.500 0.2316 0.00759 0.00266 0.0076 0.5862 0.9271 1.750 0.2617 0.00763 0.00267 0.0073 0.5760 0.9311 2.000 0.2915 0.00768 0.00271 0.0070 0.5673 0.9357 2.250 0.3173 0.00773 0.00273 0.0075 0.5599 0.9424 2.500 0.3501 0.00780 0.00279 0.0065 0.5521 0.9454 2.750 0.3827 0.00788 0.00285 0.0056 0.5431 0.9488 3.000 0.4137 0.00794 0.00292 0.0049 0.5336 0.9531 3.250 0.4421 0.00803 0.00296 0.0048 0.5246 0.9583 3.500 0.4778 0.00810 0.00303 0.0031 0.5122 0.9603 3.750 0.5134 0.00818 0.00312 0.0014 0.4990 0.9624 4.000 0.5487 0.00828 0.00319 -0.0002 0.4844 0.9649 4.250 0.5807 0.00840 0.00327 -0.0012 0.4655 0.9687 4.500 0.6119 0.00855 0.00336 -0.0020 0.4403 0.9725 4.750 0.6472 0.00879 0.00347 -0.0039 0.4048 0.9743 5.000 0.6798 0.00920 0.00367 -0.0053 0.3531 0.9770 5.250 0.7086 0.00980 0.00397 -0.0061 0.2919 0.9812 5.500 0.7381 0.01037 0.00431 -0.0071 0.2435 0.9849 5.750 0.7711 0.01091 0.00466 -0.0088 0.2048 0.9873 6.000 0.8035 0.01137 0.00499 -0.0103 0.1777 0.9904 6.250 0.8347 0.01182 0.00534 -0.0116 0.1593 0.9938 6.500 0.8687 0.01220 0.00566 -0.0134 0.1458 0.9962 6.750 0.9027 0.01253 0.00597 -0.0152 0.1357 0.9987 7.000 0.9281 0.01289 0.00632 -0.0152 0.1282 1.0000 7.250 0.9431 0.01315 0.00659 -0.0131 0.1226 1.0000 7.500 0.9553 0.01357 0.00697 -0.0104 0.1168 1.0000 7.750 0.9711 0.01381 0.00726 -0.0084 0.1133 1.0000 8.000 0.9864 0.01410 0.00758 -0.0062 0.1090 1.0000 8.250 0.9993 0.01457 0.00801 -0.0037 0.1042 1.0000 8.500 1.0153 0.01490 0.00839 -0.0017 0.1009 1.0000 8.750 1.0324 0.01521 0.00874 0.0001 0.0973 1.0000 9.000 1.0476 0.01562 0.00915 0.0021 0.0936 1.0000 9.250 1.0601 0.01621 0.00973 0.0045 0.0897 1.0000 9.500 1.0780 0.01649 0.01009 0.0061 0.0870 1.0000 9.750 1.0946 0.01685 0.01048 0.0078 0.0836 1.0000 10.000 1.1074 0.01739 0.01101 0.0100 0.0803 1.0000 10.250 1.1192 0.01799 0.01165 0.0124 0.0774 1.0000 10.500 1.1344 0.01835 0.01208 0.0143 0.0749 1.0000 10.750 1.1465 0.01877 0.01254 0.0167 0.0722 1.0000 11.000 1.1550 0.01940 0.01317 0.0194 0.0695 1.0000 11.250 1.1619 0.02024 0.01404 0.0220 0.0669 1.0000 11.500 1.1763 0.02074 0.01464 0.0235 0.0647 1.0000 11.750 1.1893 0.02137 0.01532 0.0251 0.0623 1.0000 12.000 1.1991 0.02223 0.01619 0.0267 0.0597 1.0000 12.250 1.2037 0.02352 0.01751 0.0286 0.0573 1.0000 12.500 1.2178 0.02424 0.01833 0.0295 0.0554 1.0000 12.750 1.2300 0.02514 0.01930 0.0305 0.0532 1.0000 13.000 1.2387 0.02633 0.02053 0.0315 0.0513 1.0000 13.250 1.2404 0.02813 0.02234 0.0328 0.0490 1.0000 13.500 1.2515 0.02929 0.02361 0.0334 0.0476 1.0000 13.750 1.2618 0.03052 0.02494 0.0340 0.0459 1.0000 14.000 1.2700 0.03198 0.02646 0.0345 0.0441 1.0000 14.250 1.2743 0.03383 0.02835 0.0349 0.0425 1.0000 14.500 1.2741 0.03611 0.03068 0.0355 0.0409 1.0000 14.750 1.2819 0.03777 0.03247 0.0357 0.0397 1.0000 15.000 1.2876 0.03965 0.03443 0.0358 0.0383 1.0000 15.250 1.2920 0.04169 0.03655 0.0358 0.0369 1.0000 15.500 1.2917 0.04424 0.03914 0.0356 0.0356 1.0000 15.750 1.2851 0.04745 0.04240 0.0355 0.0345 1.0000 16.000 1.2884 0.04981 0.04490 0.0352 0.0336 1.0000 16.250 1.2903 0.05240 0.04761 0.0346 0.0324 1.0000 16.500 1.2899 0.05531 0.05062 0.0339 0.0316 1.0000 16.750 1.2884 0.05847 0.05386 0.0330 0.0306 1.0000 17.000 1.2830 0.06219 0.05765 0.0318 0.0298 1.0000 17.250 1.2733 0.06651 0.06203 0.0305 0.0289 1.0000 17.500 1.2678 0.07048 0.06612 0.0291 0.0283 1.0000 17.750 1.2628 0.07459 0.07037 0.0274 0.0277 1.0000 18.000 1.2566 0.07899 0.07490 0.0255 0.0269 1.0000 18.250 1.2492 0.08365 0.07967 0.0234 0.0263 1.0000 18.500 1.2400 0.08868 0.08480 0.0210 0.0259 1.0000 18.750 1.2308 0.09393 0.09014 0.0184 0.0252 1.0000 19.000 1.2201 0.09942 0.09572 0.0156 0.0248 1.0000 19.250 1.2083 0.10515 0.10152 0.0128 0.0243 1.0000