XFOIL Version 6.96 Calculated polar for: EPPLER 638 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.2120 0.09155 0.08911 -0.0309 0.6965 0.0110 -9.750 -0.2139 0.08688 0.08442 -0.0331 0.6849 0.0111 -9.500 -0.2128 0.08281 0.08031 -0.0346 0.6726 0.0111 -9.250 -0.2123 0.07863 0.07609 -0.0362 0.6615 0.0111 -9.000 -0.2120 0.07461 0.07203 -0.0376 0.6505 0.0111 -8.250 -0.2264 0.06086 0.05825 -0.0430 0.6241 0.0114 -8.000 -0.2376 0.05635 0.05374 -0.0463 0.6172 0.0113 -7.750 -0.2525 0.05249 0.04985 -0.0477 0.6097 0.0114 -7.500 -0.2595 0.04912 0.04642 -0.0476 0.6016 0.0114 -7.250 -0.2597 0.04572 0.04295 -0.0479 0.5927 0.0115 -7.000 -0.2574 0.04223 0.03938 -0.0480 0.5842 0.0116 -6.750 -0.2524 0.03893 0.03599 -0.0479 0.5751 0.0117 -6.500 -0.2458 0.03552 0.03249 -0.0477 0.5670 0.0119 -6.250 -0.2372 0.03224 0.02908 -0.0473 0.5589 0.0121 -6.000 -0.2274 0.02873 0.02544 -0.0467 0.5517 0.0123 -5.750 -0.2159 0.02541 0.02196 -0.0458 0.5441 0.0127 -5.500 -0.2374 0.02457 0.01989 -0.0414 0.5560 0.0114 -5.250 -0.2169 0.02357 0.01875 -0.0405 0.5465 0.0117 -5.000 -0.2099 0.01677 0.01099 -0.0358 0.5412 0.0114 -4.750 -0.1861 0.01594 0.01003 -0.0351 0.5323 0.0118 -4.500 -0.1607 0.01560 0.00961 -0.0346 0.5234 0.0121 -4.250 -0.1355 0.01502 0.00889 -0.0340 0.5144 0.0125 -4.000 -0.1098 0.01433 0.00803 -0.0334 0.5062 0.0134 -3.750 -0.0839 0.01360 0.00709 -0.0326 0.4982 0.0141 -3.500 -0.0589 0.01245 0.00577 -0.0319 0.4913 0.0148 -3.250 -0.0328 0.01211 0.00539 -0.0315 0.4838 0.0155 -3.000 -0.0065 0.01181 0.00504 -0.0311 0.4769 0.0162 -2.750 0.0198 0.01145 0.00461 -0.0306 0.4697 0.0171 -2.500 0.0466 0.01131 0.00437 -0.0302 0.4630 0.0180 -2.250 0.0710 0.01067 0.00371 -0.0294 0.4568 0.0193 -2.000 0.0968 0.01048 0.00347 -0.0289 0.4504 0.0204 -1.750 0.1231 0.01024 0.00322 -0.0285 0.4451 0.0216 -1.500 0.1493 0.01007 0.00299 -0.0280 0.4391 0.0225 -1.250 0.1741 0.00975 0.00261 -0.0273 0.4337 0.0239 -1.000 0.2001 0.00954 0.00239 -0.0268 0.4285 0.0254 -0.750 0.2263 0.00942 0.00223 -0.0263 0.4233 0.0268 -0.500 0.2528 0.00933 0.00210 -0.0260 0.4186 0.0282 -0.250 0.2794 0.00919 0.00193 -0.0256 0.4141 0.0305 0.000 0.3059 0.00912 0.00183 -0.0252 0.4093 0.0337 0.250 0.3324 0.00907 0.00176 -0.0248 0.4045 0.0406 0.500 0.3549 0.00853 0.00173 -0.0239 0.4012 0.2211 0.750 0.3495 0.00645 0.00177 -0.0171 0.3985 0.8969 1.000 0.3909 0.00667 0.00203 -0.0195 0.3939 0.9575 1.250 0.4366 0.00695 0.00223 -0.0231 0.3890 0.9670 1.500 0.4884 0.00720 0.00242 -0.0280 0.3848 0.9741 1.750 0.5400 0.00742 0.00257 -0.0330 0.3803 0.9785 2.000 0.5831 0.00767 0.00273 -0.0362 0.3759 0.9844 2.250 0.6182 0.00770 0.00273 -0.0378 0.3728 0.9853 2.500 0.6519 0.00773 0.00274 -0.0392 0.3693 0.9864 2.750 0.6849 0.00778 0.00276 -0.0404 0.3657 0.9876 3.000 0.7170 0.00787 0.00279 -0.0414 0.3622 0.9890 3.250 0.7486 0.00795 0.00285 -0.0424 0.3590 0.9906 3.500 0.7799 0.00799 0.00289 -0.0432 0.3563 0.9923 3.750 0.8099 0.00806 0.00295 -0.0438 0.3529 0.9940 4.000 0.8426 0.00812 0.00298 -0.0450 0.3497 0.9949 4.250 0.8748 0.00822 0.00305 -0.0462 0.3459 0.9960 4.500 0.9075 0.00825 0.00309 -0.0474 0.3434 0.9972 4.750 0.9398 0.00829 0.00314 -0.0486 0.3404 0.9984 5.000 0.9717 0.00835 0.00320 -0.0496 0.3373 0.9995 5.250 0.9995 0.00845 0.00328 -0.0499 0.3340 1.0000 5.500 1.0223 0.00859 0.00340 -0.0490 0.3302 1.0000 5.750 1.0462 0.00863 0.00349 -0.0484 0.3277 1.0000 6.000 1.0699 0.00870 0.00358 -0.0477 0.3243 1.0000 6.250 1.0929 0.00881 0.00368 -0.0469 0.3208 1.0000 6.500 1.1151 0.00898 0.00384 -0.0460 0.3167 1.0000 6.750 1.1387 0.00905 0.00395 -0.0453 0.3137 1.0000 7.000 1.1620 0.00913 0.00407 -0.0446 0.3099 1.0000 7.250 1.1846 0.00927 0.00421 -0.0437 0.3058 1.0000 7.500 1.2063 0.00946 0.00439 -0.0428 0.3015 1.0000 7.750 1.2297 0.00954 0.00452 -0.0421 0.2982 1.0000 8.000 1.2524 0.00967 0.00467 -0.0412 0.2939 1.0000 8.250 1.2738 0.00986 0.00487 -0.0402 0.2888 1.0000 8.500 1.2963 0.00999 0.00504 -0.0394 0.2844 1.0000 8.750 1.3184 0.01015 0.00521 -0.0385 0.2789 1.0000 9.000 1.3389 0.01039 0.00545 -0.0374 0.2734 1.0000 9.250 1.3613 0.01052 0.00564 -0.0366 0.2686 1.0000 9.500 1.3819 0.01075 0.00587 -0.0355 0.2622 1.0000 9.750 1.4027 0.01097 0.00611 -0.0344 0.2560 1.0000 10.000 1.4225 0.01123 0.00638 -0.0332 0.2481 1.0000 10.250 1.4419 0.01150 0.00666 -0.0319 0.2390 1.0000 10.500 1.4595 0.01186 0.00699 -0.0304 0.2276 1.0000 10.750 1.4755 0.01229 0.00738 -0.0286 0.2133 1.0000 11.000 1.4900 0.01279 0.00783 -0.0266 0.1984 1.0000 11.250 1.4991 0.01352 0.00845 -0.0238 0.1774 1.0000 11.500 1.5079 0.01423 0.00907 -0.0210 0.1588 1.0000 11.750 1.5150 0.01497 0.00974 -0.0179 0.1434 1.0000 12.000 1.5125 0.01594 0.01060 -0.0133 0.1248 1.0000 12.250 1.5111 0.01673 0.01136 -0.0089 0.1133 1.0000 12.500 1.5121 0.01761 0.01221 -0.0053 0.1029 1.0000 12.750 1.5126 0.01868 0.01327 -0.0022 0.0930 1.0000 13.000 1.5128 0.01996 0.01456 0.0004 0.0844 1.0000 13.250 1.5113 0.02160 0.01620 0.0025 0.0768 1.0000 13.500 1.5118 0.02340 0.01802 0.0037 0.0701 1.0000 13.750 1.5093 0.02569 0.02034 0.0046 0.0632 1.0000 14.000 1.5070 0.02822 0.02291 0.0050 0.0583 1.0000 14.250 1.5041 0.03096 0.02569 0.0051 0.0537 1.0000 14.500 1.4977 0.03416 0.02894 0.0051 0.0492 1.0000 14.750 1.4897 0.03762 0.03245 0.0049 0.0452 1.0000 15.000 1.4829 0.04098 0.03589 0.0047 0.0424 1.0000 15.250 1.4734 0.04468 0.03965 0.0043 0.0401 1.0000 15.500 1.4607 0.04878 0.04381 0.0039 0.0370 1.0000 15.750 1.4509 0.05259 0.04770 0.0034 0.0349 1.0000 16.000 1.4386 0.05682 0.05200 0.0028 0.0326 1.0000 16.250 1.4248 0.06137 0.05660 0.0019 0.0302 1.0000 16.500 1.4160 0.06535 0.06065 0.0012 0.0284 1.0000 16.750 1.4023 0.07005 0.06540 0.0002 0.0256 1.0000 17.000 1.3906 0.07453 0.06994 -0.0009 0.0236 1.0000 17.250 1.3821 0.07866 0.07412 -0.0018 0.0219 1.0000 17.500 1.3715 0.08312 0.07864 -0.0029 0.0200 1.0000 17.750 1.3599 0.08780 0.08337 -0.0042 0.0179 1.0000 18.000 1.3501 0.09225 0.08787 -0.0054 0.0162 1.0000 18.250 1.3395 0.09687 0.09253 -0.0067 0.0144 1.0000 18.500 1.3315 0.10120 0.09692 -0.0080 0.0130 1.0000 18.750 1.3199 0.10606 0.10183 -0.0095 0.0113 1.0000 19.000 1.3100 0.11074 0.10655 -0.0111 0.0092 1.0000