XFOIL Version 6.96 Calculated polar for: EPPLER 541 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 ------ -------- --------- --------- -------- -------- -------- -12.750 -0.4101 0.11114 0.10628 -0.0645 1.0000 0.0159 -12.500 -0.4198 0.10709 0.10233 -0.0649 1.0000 0.0157 -12.250 -0.4326 0.10253 0.09785 -0.0655 0.9991 0.0155 -12.000 -0.4358 0.09332 0.08863 -0.0725 0.9915 0.0153 -11.750 -0.4482 0.08424 0.07946 -0.0799 0.9838 0.0151 -11.500 -0.4606 0.07758 0.07271 -0.0851 0.9758 0.0148 -11.250 -0.4749 0.07135 0.06631 -0.0894 0.9694 0.0146 -11.000 -0.4916 0.06585 0.06057 -0.0917 0.9616 0.0146 -10.750 -0.5020 0.06096 0.05540 -0.0936 0.9560 0.0145 -10.500 -0.5110 0.05702 0.05119 -0.0938 0.9481 0.0143 -10.250 -0.5141 0.05327 0.04711 -0.0941 0.9422 0.0141 -10.000 -0.5211 0.04988 0.04337 -0.0924 0.9335 0.0142 -9.750 -0.5205 0.04660 0.03964 -0.0912 0.9277 0.0143 -9.500 -0.5212 0.04427 0.03698 -0.0886 0.9197 0.0142 -9.250 -0.5143 0.04166 0.03394 -0.0867 0.9145 0.0147 -9.000 -0.5058 0.03952 0.03144 -0.0846 0.9086 0.0149 -8.750 -0.4913 0.03757 0.02903 -0.0831 0.9035 0.0157 -8.500 -0.4687 0.03517 0.02637 -0.0833 0.9004 0.0171 -8.250 -0.4436 0.03350 0.02450 -0.0836 0.8971 0.0182 -8.000 -0.4117 0.03174 0.02253 -0.0846 0.8941 0.0190 -7.750 -0.3734 0.02998 0.02055 -0.0862 0.8923 0.0206 -7.500 -0.3412 0.02869 0.01907 -0.0870 0.8899 0.0220 -7.250 -0.3155 0.02749 0.01780 -0.0870 0.8872 0.0250 -7.000 -0.2925 0.02662 0.01687 -0.0867 0.8844 0.0297 -6.750 -0.2800 0.02608 0.01620 -0.0844 0.8790 0.0325 -6.500 -0.2644 0.02523 0.01536 -0.0827 0.8749 0.0409 -6.250 -0.2454 0.02440 0.01456 -0.0816 0.8720 0.0579 -6.000 -0.2303 0.02367 0.01415 -0.0798 0.8686 0.1001 -5.750 -0.2214 0.02299 0.01406 -0.0770 0.8641 0.1963 -5.500 -0.2024 0.02286 0.01601 -0.0732 0.8619 0.5458 -5.000 -0.1537 0.02573 0.01873 -0.0683 0.8566 0.6965 -4.750 -0.1403 0.02681 0.01967 -0.0649 0.8520 0.7153 -4.500 -0.1275 0.02761 0.02033 -0.0616 0.8481 0.7328 -4.250 -0.0959 0.02883 0.02134 -0.0609 0.8459 0.7528 -4.000 -0.0429 0.02991 0.02220 -0.0640 0.8452 0.7684 -3.750 -0.0269 0.02998 0.02212 -0.0621 0.8426 0.7789 -3.500 0.0051 0.03011 0.02211 -0.0630 0.8399 0.7823 -3.000 0.0321 0.03033 0.02213 -0.0587 0.8323 0.7948 -2.750 0.0645 0.03020 0.02186 -0.0600 0.8303 0.7979 -2.500 0.0575 0.03036 0.02197 -0.0541 0.8259 0.8067 -2.250 0.0808 0.03050 0.02204 -0.0538 0.8222 0.8092 -2.000 0.1051 0.03049 0.02194 -0.0536 0.8191 0.8123 -1.750 0.1217 0.03042 0.02180 -0.0521 0.8163 0.8169 -1.500 0.1327 0.03029 0.02159 -0.0495 0.8140 0.8218 -1.250 0.1360 0.03078 0.02209 -0.0456 0.8076 0.8252 -1.000 0.1510 0.03082 0.02207 -0.0437 0.8041 0.8287 -0.750 0.1440 0.03071 0.02191 -0.0377 0.8005 0.8350 -0.500 0.1458 0.03119 0.02241 -0.0335 0.7939 0.8378 -0.250 0.1624 0.03123 0.02241 -0.0320 0.7902 0.8403 0.000 0.1818 0.03108 0.02222 -0.0309 0.7876 0.8431 0.500 0.1589 0.03144 0.02256 -0.0175 0.7747 0.8515 0.750 0.1900 0.03123 0.02232 -0.0186 0.7728 0.8529 1.250 0.1678 0.03134 0.02242 -0.0055 0.7593 0.8609 1.500 0.1873 0.03099 0.02204 -0.0044 0.7569 0.8628 1.750 0.1716 0.03147 0.02255 0.0026 0.7466 0.8656 2.000 0.2037 0.03121 0.02228 0.0015 0.7446 0.8666 2.500 0.2157 0.03128 0.02237 0.0079 0.7316 0.8707 2.750 0.2483 0.03090 0.02200 0.0069 0.7297 0.8718 3.250 0.2644 0.03080 0.02193 0.0124 0.7163 0.8760 4.000 0.3279 0.03046 0.02173 0.0146 0.7001 0.8793 4.250 0.3333 0.03074 0.02206 0.0175 0.6900 0.8812 4.500 0.3689 0.03022 0.02160 0.0163 0.6876 0.8817 5.000 0.4091 0.02993 0.02147 0.0180 0.6737 0.8840 5.250 0.4165 0.03021 0.02182 0.0204 0.6623 0.8856 5.500 0.4437 0.02982 0.02151 0.0204 0.6567 0.8867 5.750 0.4626 0.02970 0.02147 0.0214 0.6476 0.8884 6.250 0.5114 0.02899 0.02099 0.0221 0.6322 0.8906 6.500 0.5256 0.02908 0.02118 0.0237 0.6200 0.8918 6.750 0.5430 0.02903 0.02125 0.0249 0.6080 0.8929 7.000 0.5634 0.02884 0.02118 0.0257 0.5959 0.8940 7.250 0.5855 0.02860 0.02109 0.0264 0.5831 0.8951 7.500 0.6080 0.02833 0.02094 0.0271 0.5686 0.8963 7.750 0.6332 0.02795 0.02066 0.0275 0.5525 0.8976 8.000 0.6640 0.02722 0.02003 0.0275 0.5343 0.8988 8.250 0.6923 0.02670 0.01959 0.0277 0.5098 0.9002 8.500 0.7248 0.02602 0.01887 0.0275 0.4784 0.9013 8.750 0.7499 0.02588 0.01861 0.0280 0.4403 0.9024 9.000 0.7682 0.02618 0.01877 0.0290 0.4006 0.9037 9.250 0.7805 0.02678 0.01924 0.0307 0.3636 0.9050 9.500 0.7897 0.02760 0.01994 0.0325 0.3272 0.9064 9.750 0.7975 0.02856 0.02079 0.0342 0.2928 0.9080 10.000 0.8046 0.02965 0.02179 0.0359 0.2590 0.9097 10.250 0.8119 0.03080 0.02284 0.0373 0.2274 0.9114 10.500 0.8189 0.03205 0.02399 0.0386 0.1974 0.9133 10.750 0.8260 0.03337 0.02521 0.0399 0.1690 0.9154 11.250 0.8391 0.03616 0.02784 0.0422 0.1214 0.9194 11.500 0.8465 0.03757 0.02923 0.0433 0.1027 0.9214 11.750 0.8535 0.03908 0.03074 0.0442 0.0879 0.9233 12.000 0.8601 0.04071 0.03239 0.0451 0.0755 0.9253 12.250 0.8664 0.04242 0.03413 0.0459 0.0654 0.9274 12.500 0.8708 0.04434 0.03609 0.0466 0.0578 0.9295 13.000 0.8799 0.04831 0.04021 0.0479 0.0472 0.9339 13.250 0.8880 0.05010 0.04221 0.0484 0.0425 0.9363 13.500 0.8926 0.05222 0.04443 0.0487 0.0383 0.9391 13.750 0.8961 0.05457 0.04685 0.0490 0.0353 0.9420 14.000 0.9033 0.05668 0.04918 0.0492 0.0320 0.9452 14.250 0.9073 0.05907 0.05171 0.0490 0.0291 0.9489 14.500 0.9083 0.06192 0.05462 0.0488 0.0269 0.9528 14.750 0.9142 0.06452 0.05745 0.0485 0.0249 0.9571 15.000 0.9176 0.06747 0.06065 0.0477 0.0225 0.9617 15.250 0.9189 0.07072 0.06406 0.0465 0.0208 0.9673 15.500 0.9189 0.07404 0.06753 0.0452 0.0198 0.9761 15.750 0.9155 0.07755 0.07116 0.0444 0.0189 1.0000 16.000 0.9132 0.08168 0.07554 0.0433 0.0181 1.0000 16.250 0.9082 0.08637 0.08052 0.0414 0.0173 1.0000 16.500 0.9011 0.09147 0.08588 0.0392 0.0168 1.0000 16.750 0.8921 0.09706 0.09171 0.0365 0.0163 1.0000 17.000 0.8801 0.10338 0.09827 0.0330 0.0157 1.0000 17.250 0.8679 0.11002 0.10513 0.0292 0.0156 1.0000 17.500 0.8518 0.11782 0.11314 0.0247 0.0157 1.0000 17.750 0.8336 0.12646 0.12199 0.0194 0.0158 1.0000 18.000 0.8117 0.13656 0.13222 0.0131 0.0164 1.0000 18.250 0.7849 0.14882 0.14463 0.0058 0.0169 1.0000