XFOIL Version 6.96 Calculated polar for: EPPLER 549 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.7182 0.12180 0.11936 -0.0414 1.0000 0.0024 -18.000 -0.7503 0.11089 0.10831 -0.0467 1.0000 0.0024 -17.750 -0.7910 0.09866 0.09587 -0.0529 1.0000 0.0024 -17.500 -0.8071 0.09163 0.08873 -0.0565 1.0000 0.0024 -17.250 -0.8242 0.08467 0.08164 -0.0600 1.0000 0.0024 -17.000 -0.8462 0.07730 0.07411 -0.0636 1.0000 0.0024 -16.750 -0.8555 0.07233 0.06903 -0.0659 1.0000 0.0024 -16.500 -0.8662 0.06737 0.06395 -0.0679 1.0000 0.0024 -16.250 -0.8772 0.06269 0.05913 -0.0696 1.0000 0.0024 -16.000 -0.8854 0.05862 0.05495 -0.0708 1.0000 0.0024 -15.750 -0.8879 0.05542 0.05166 -0.0716 1.0000 0.0024 -15.500 -0.8960 0.05173 0.04784 -0.0722 1.0000 0.0024 -15.250 -0.8986 0.04883 0.04484 -0.0724 1.0000 0.0024 -15.000 -0.8979 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-0.0706 0.5297 0.5659 -0.500 0.2767 0.00733 0.00167 -0.0708 0.5249 0.5671 -0.250 0.3051 0.00737 0.00167 -0.0711 0.5206 0.5682 0.000 0.3339 0.00740 0.00168 -0.0714 0.5167 0.5692 0.250 0.3623 0.00743 0.00169 -0.0716 0.5121 0.5703 0.500 0.3903 0.00747 0.00171 -0.0718 0.5076 0.5717 0.750 0.4187 0.00750 0.00174 -0.0720 0.5037 0.5732 1.000 0.4472 0.00753 0.00177 -0.0723 0.4997 0.5747 1.250 0.4754 0.00758 0.00181 -0.0725 0.4957 0.5760 1.500 0.5033 0.00764 0.00185 -0.0727 0.4920 0.5773 1.750 0.5317 0.00768 0.00190 -0.0729 0.4888 0.5787 2.000 0.5600 0.00772 0.00194 -0.0731 0.4851 0.5800 2.250 0.5880 0.00778 0.00199 -0.0733 0.4809 0.5814 2.500 0.6154 0.00786 0.00206 -0.0734 0.4764 0.5827 2.750 0.6437 0.00791 0.00211 -0.0736 0.4727 0.5839 3.000 0.6717 0.00797 0.00217 -0.0738 0.4687 0.5850 3.250 0.6993 0.00803 0.00225 -0.0739 0.4648 0.5867 3.500 0.7263 0.00811 0.00233 -0.0740 0.4603 0.5884 3.750 0.7541 0.00817 0.00241 -0.0741 0.4555 0.5901 4.000 0.7811 0.00825 0.00250 -0.0741 0.4491 0.5917 4.250 0.8080 0.00835 0.00260 -0.0741 0.4431 0.5933 4.500 0.8349 0.00844 0.00269 -0.0741 0.4361 0.5950 4.750 0.8610 0.00856 0.00281 -0.0740 0.4279 0.5966 5.000 0.8869 0.00870 0.00292 -0.0738 0.4175 0.5982 5.250 0.9130 0.00882 0.00304 -0.0737 0.4090 0.5997 5.750 0.9632 0.00913 0.00333 -0.0731 0.3880 0.6029 6.000 0.9873 0.00931 0.00350 -0.0726 0.3748 0.6049 6.250 1.0099 0.00957 0.00371 -0.0719 0.3577 0.6071 6.500 1.0307 0.00989 0.00395 -0.0708 0.3338 0.6093 6.750 1.0473 0.01039 0.00429 -0.0691 0.2993 0.6115 7.000 1.0650 0.01081 0.00462 -0.0675 0.2799 0.6135 7.250 1.0844 0.01114 0.00492 -0.0663 0.2683 0.6154 7.750 1.1209 0.01167 0.00544 -0.0632 0.2486 0.6195 8.000 1.1363 0.01202 0.00576 -0.0612 0.2327 0.6219 8.250 1.1483 0.01252 0.00617 -0.0586 0.2097 0.6243 8.500 1.1584 0.01309 0.00665 -0.0559 0.1892 0.6268 8.750 1.1697 0.01364 0.00714 -0.0534 0.1733 0.6293 9.000 1.1792 0.01426 0.00769 -0.0507 0.1563 0.6317 9.250 1.1883 0.01490 0.00829 -0.0480 0.1413 0.6342 9.500 1.1978 0.01555 0.00892 -0.0456 0.1286 0.6373 9.750 1.2067 0.01626 0.00960 -0.0432 0.1168 0.6406 10.000 1.2152 0.01704 0.01035 -0.0409 0.1062 0.6441 10.250 1.2228 0.01790 0.01119 -0.0386 0.0961 0.6474 10.500 1.2294 0.01886 0.01213 -0.0363 0.0854 0.6507 10.750 1.2371 0.01983 0.01310 -0.0343 0.0765 0.6544 11.000 1.2443 0.02088 0.01414 -0.0324 0.0688 0.6583 11.250 1.2500 0.02207 0.01533 -0.0304 0.0612 0.6622 11.500 1.2571 0.02324 0.01651 -0.0288 0.0545 0.6660 11.750 1.2636 0.02450 0.01780 -0.0272 0.0491 0.6706 12.000 1.2684 0.02593 0.01923 -0.0257 0.0429 0.6754 12.500 1.2822 0.02867 0.02204 -0.0232 0.0355 0.6853 12.750 1.2856 0.03037 0.02375 -0.0219 0.0302 0.6912 13.250 1.2958 0.03367 0.02715 -0.0199 0.0240 0.7049 13.750 1.3031 0.03744 0.03100 -0.0182 0.0180 0.7208 14.000 1.3081 0.03930 0.03292 -0.0176 0.0166 0.7296 14.250 1.3133 0.04119 0.03488 -0.0171 0.0149 0.7401 14.500 1.3173 0.04324 0.03700 -0.0166 0.0135 0.7514 14.750 1.3220 0.04526 0.03911 -0.0162 0.0124 0.7649 15.000 1.3265 0.04733 0.04128 -0.0159 0.0112 0.7817 15.250 1.3296 0.04957 0.04364 -0.0156 0.0102 0.8046 15.500 1.3327 0.05168 0.04592 -0.0152 0.0095 0.8437 16.000 1.3447 0.05645 0.05107 -0.0164 0.0078 1.0000 16.250 1.3477 0.05903 0.05370 -0.0167 0.0074 1.0000 16.500 1.3511 0.06160 0.05632 -0.0169 0.0067 1.0000 16.750 1.3530 0.06440 0.05917 -0.0173 0.0061 1.0000 17.000 1.3542 0.06734 0.06217 -0.0178 0.0057 1.0000 17.250 1.3564 0.07021 0.06510 -0.0183 0.0053 1.0000 17.500 1.3580 0.07321 0.06817 -0.0190 0.0050 1.0000 17.750 1.3590 0.07634 0.07137 -0.0197 0.0047 1.0000 18.000 1.3591 0.07962 0.07471 -0.0206 0.0043 1.0000 18.250 1.3581 0.08313 0.07828 -0.0216 0.0040 1.0000 18.500 1.3583 0.08652 0.08175 -0.0226 0.0039 1.0000 18.750 1.3574 0.09011 0.08542 -0.0238 0.0034 1.0000 19.000 1.3567 0.09372 0.08910 -0.0250 0.0033 1.0000 19.250 1.3544 0.09764 0.09310 -0.0264 0.0031 1.0000