XFOIL Version 6.96 Calculated polar for: EPPLER 637 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3535 0.09454 0.09017 -0.0178 1.0000 0.0502 -8.250 -0.3541 0.09102 0.08672 -0.0202 1.0000 0.0513 -8.000 -0.3605 0.08726 0.08306 -0.0244 1.0000 0.0525 -7.750 -0.3746 0.08389 0.07975 -0.0280 1.0000 0.0533 -7.500 -0.3862 0.08099 0.07683 -0.0302 1.0000 0.0537 -7.250 -0.3775 0.07681 0.07237 -0.0354 0.9044 0.0540 -7.000 -0.3530 0.07038 0.06593 -0.0379 0.8554 0.0550 -6.750 -0.3404 0.06692 0.06232 -0.0380 0.8167 0.0558 -6.500 -0.3322 0.06393 0.05914 -0.0375 0.7873 0.0567 -6.250 -0.3244 0.06094 0.05597 -0.0370 0.7634 0.0576 -5.750 -0.3079 0.04987 0.04396 -0.0350 0.7320 0.0294 -5.500 -0.2954 0.04722 0.04112 -0.0338 0.7152 0.0286 -5.250 -0.2821 0.04435 0.03797 -0.0324 0.7002 0.0276 -5.000 -0.2676 0.04133 0.03457 -0.0307 0.6867 0.0267 -4.500 -0.2337 0.03627 0.02875 -0.0274 0.6611 0.0273 -4.250 -0.2146 0.03390 0.02596 -0.0257 0.6491 0.0279 -4.000 -0.1942 0.03165 0.02327 -0.0241 0.6381 0.0276 -3.750 -0.1723 0.02952 0.02070 -0.0225 0.6271 0.0272 -3.500 -0.1487 0.02760 0.01835 -0.0212 0.6162 0.0271 -3.250 -0.1238 0.02592 0.01626 -0.0201 0.6063 0.0272 -3.000 -0.0976 0.02444 0.01444 -0.0192 0.5959 0.0275 -2.750 -0.0705 0.02315 0.01287 -0.0185 0.5859 0.0280 -2.500 -0.0433 0.02207 0.01150 -0.0178 0.5770 0.0292 -2.250 -0.0172 0.02123 0.01061 -0.0174 0.5673 0.0317 -2.000 0.0086 0.02050 0.00974 -0.0167 0.5592 0.0340 -1.750 0.0337 0.01975 0.00888 -0.0158 0.5501 0.0357 -1.500 0.0570 0.01910 0.00816 -0.0147 0.5427 0.0381 -1.250 0.0810 0.01866 0.00763 -0.0137 0.5344 0.0426 -1.000 0.1052 0.01825 0.00711 -0.0128 0.5279 0.0519 -0.750 0.3030 0.01568 0.00711 -0.0435 0.5106 1.0000 -0.500 0.3259 0.01571 0.00694 -0.0428 0.5032 1.0000 -0.250 0.3488 0.01576 0.00676 -0.0419 0.4974 1.0000 0.000 0.3718 0.01582 0.00667 -0.0412 0.4909 1.0000 0.250 0.3949 0.01589 0.00658 -0.0404 0.4846 1.0000 0.500 0.4180 0.01598 0.00648 -0.0396 0.4794 1.0000 0.750 0.4413 0.01607 0.00649 -0.0389 0.4731 1.0000 1.000 0.4646 0.01618 0.00647 -0.0381 0.4678 1.0000 1.250 0.4879 0.01631 0.00646 -0.0374 0.4630 1.0000 1.500 0.5112 0.01645 0.00654 -0.0366 0.4571 1.0000 1.750 0.5344 0.01659 0.00658 -0.0359 0.4521 1.0000 2.000 0.5577 0.01676 0.00663 -0.0351 0.4480 1.0000 2.250 0.5808 0.01695 0.00682 -0.0344 0.4426 1.0000 2.500 0.6039 0.01713 0.00695 -0.0336 0.4378 1.0000 2.750 0.6272 0.01732 0.00703 -0.0328 0.4339 1.0000 3.000 0.6500 0.01756 0.00728 -0.0320 0.4290 1.0000 3.250 0.6729 0.01780 0.00752 -0.0313 0.4243 1.0000 3.500 0.6960 0.01802 0.00769 -0.0305 0.4203 1.0000 3.750 0.7190 0.01826 0.00787 -0.0297 0.4165 1.0000 4.000 0.7413 0.01856 0.00825 -0.0289 0.4116 1.0000 4.250 0.7639 0.01884 0.00854 -0.0280 0.4075 1.0000 4.500 0.7869 0.01910 0.00876 -0.0272 0.4039 1.0000 4.750 0.8094 0.01941 0.00908 -0.0264 0.4000 1.0000 5.000 0.8310 0.01977 0.00954 -0.0255 0.3953 1.0000 5.250 0.8533 0.02008 0.00988 -0.0247 0.3913 1.0000 5.500 0.8761 0.02038 0.01015 -0.0238 0.3880 1.0000 5.750 0.8978 0.02076 0.01061 -0.0229 0.3842 1.0000 6.000 0.9186 0.02118 0.01115 -0.0220 0.3795 1.0000 6.250 0.9404 0.02153 0.01156 -0.0210 0.3756 1.0000 6.500 0.9630 0.02185 0.01187 -0.0202 0.3724 1.0000 6.750 0.9836 0.02231 0.01246 -0.0192 0.3684 1.0000 7.000 1.0033 0.02280 0.01309 -0.0181 0.3638 1.0000 7.250 1.0245 0.02318 0.01354 -0.0171 0.3599 1.0000 7.500 1.0472 0.02349 0.01387 -0.0163 0.3566 1.0000 7.750 1.0654 0.02408 0.01464 -0.0151 0.3520 1.0000 8.000 1.0840 0.02460 0.01530 -0.0138 0.3473 1.0000 8.250 1.1053 0.02494 0.01570 -0.0129 0.3434 1.0000 8.500 1.1261 0.02532 0.01616 -0.0118 0.3394 1.0000 8.750 1.1413 0.02600 0.01707 -0.0102 0.3338 1.0000 9.000 1.1611 0.02633 0.01749 -0.0091 0.3290 1.0000 9.250 1.1817 0.02664 0.01786 -0.0080 0.3245 1.0000 9.500 1.1944 0.02735 0.01882 -0.0061 0.3182 1.0000 9.750 1.2140 0.02759 0.01913 -0.0049 0.3131 1.0000 10.000 1.2287 0.02814 0.01984 -0.0033 0.3074 1.0000 10.250 1.2419 0.02871 0.02060 -0.0014 0.3012 1.0000 10.500 1.2622 0.02882 0.02072 -0.0002 0.2960 1.0000 10.750 1.2673 0.02978 0.02196 0.0024 0.2890 1.0000 11.000 1.2835 0.03000 0.02225 0.0040 0.2829 1.0000 11.250 1.2870 0.03094 0.02341 0.0067 0.2759 1.0000 11.500 1.2972 0.03137 0.02393 0.0089 0.2692 1.0000 11.750 1.2947 0.03244 0.02518 0.0122 0.2622 1.0000 12.000 1.2954 0.03321 0.02602 0.0152 0.2554 1.0000 12.250 1.2883 0.03477 0.02774 0.0179 0.2486 1.0000 12.500 1.2856 0.03626 0.02931 0.0197 0.2414 1.0000 12.750 1.2741 0.03890 0.03210 0.0208 0.2343 1.0000 13.000 1.2707 0.04100 0.03425 0.0215 0.2266 1.0000 13.250 1.2502 0.04533 0.03875 0.0211 0.2189 1.0000 13.500 1.2448 0.04812 0.04156 0.0211 0.2112 1.0000 13.750 1.2206 0.05352 0.04709 0.0198 0.2035 1.0000 14.000 1.2090 0.05744 0.05107 0.0191 0.1956 1.0000 14.250 1.1954 0.06174 0.05541 0.0181 0.1873 1.0000 14.500 1.1770 0.06690 0.06065 0.0167 0.1794 1.0000 14.750 1.1737 0.06988 0.06362 0.0162 0.1710 1.0000 15.000 1.1580 0.07497 0.06878 0.0147 0.1628 1.0000 15.250 1.1502 0.07895 0.07278 0.0136 0.1547 1.0000 15.500 1.1497 0.08177 0.07556 0.0130 0.1465 1.0000 15.750 1.1353 0.08714 0.08103 0.0112 0.1390 1.0000 16.000 1.1337 0.09032 0.08418 0.0103 0.1317 1.0000 16.250 1.1248 0.09490 0.08883 0.0087 0.1245 1.0000 16.500 1.1204 0.09874 0.09268 0.0075 0.1177 1.0000 16.750 1.1149 0.10284 0.09681 0.0061 0.1110 1.0000 17.000 1.1082 0.10729 0.10129 0.0044 0.1046 1.0000 17.250 1.1042 0.11121 0.10521 0.0029 0.0979 1.0000 17.500 1.0955 0.11624 0.11031 0.0008 0.0920 1.0000 17.750 1.0920 0.12017 0.11420 -0.0008 0.0857 1.0000