XFOIL Version 6.96 Calculated polar for: EPPLER 336 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3416 0.09400 0.09099 -0.0150 1.0000 0.0394 -9.500 -0.3416 0.09003 0.08705 -0.0162 1.0000 0.0402 -9.250 -0.3439 0.08574 0.08279 -0.0178 1.0000 0.0410 -9.000 -0.3485 0.08114 0.07823 -0.0198 1.0000 0.0417 -8.750 -0.4719 0.07948 0.07627 -0.0276 1.0000 0.0380 -8.500 -0.4736 0.07646 0.07327 -0.0269 1.0000 0.0384 -8.250 -0.4790 0.07361 0.07042 -0.0256 1.0000 0.0389 -8.000 -0.4878 0.07084 0.06765 -0.0238 1.0000 0.0393 -7.750 -0.4925 0.06794 0.06472 -0.0222 1.0000 0.0400 -7.500 -0.4958 0.06505 0.06179 -0.0205 1.0000 0.0408 -7.250 -0.4988 0.06210 0.05875 -0.0184 1.0000 0.0422 -7.000 -0.5129 0.06073 0.05691 -0.0134 1.0000 0.0449 -6.750 -0.5212 0.05768 0.05367 -0.0095 0.9989 0.0454 -6.500 -0.4865 0.05168 0.04786 -0.0145 0.9606 0.0468 -6.250 -0.4476 0.04784 0.04383 -0.0192 0.9066 0.0495 -5.750 -0.4164 0.04209 0.03717 -0.0165 0.8226 0.0567 -5.500 -0.4019 0.04007 0.03498 -0.0147 0.7944 0.0588 -5.000 -0.3763 0.03618 0.03035 -0.0094 0.7528 0.0686 -4.750 -0.3583 0.03438 0.02840 -0.0079 0.7347 0.0721 -4.500 -0.3437 0.03280 0.02639 -0.0052 0.7189 0.0813 -4.250 -0.3234 0.03097 0.02444 -0.0039 0.7036 0.0852 -4.000 -0.2802 0.02246 0.01404 0.0013 0.6937 0.0252 -3.750 -0.2509 0.02081 0.01217 0.0016 0.6792 0.0249 -3.500 -0.2213 0.01948 0.01061 0.0018 0.6656 0.0250 -3.250 -0.1917 0.01805 0.00910 0.0019 0.6530 0.0259 -3.000 -0.1658 0.01728 0.00828 0.0025 0.6404 0.0281 -2.750 -0.1414 0.01660 0.00759 0.0033 0.6282 0.0329 -2.500 -0.1178 0.01603 0.00693 0.0045 0.6172 0.0368 -2.250 -0.0969 0.01534 0.00619 0.0061 0.6071 0.0448 -2.000 -0.0493 0.01256 0.00689 0.0040 0.5951 0.8517 -1.750 0.0831 0.01609 0.00986 -0.0111 0.5761 0.9361 -1.500 0.1769 0.01623 0.00962 -0.0230 0.5593 0.9664 -1.250 0.2458 0.01567 0.00881 -0.0311 0.5444 0.9868 -1.000 0.2844 0.01530 0.00828 -0.0336 0.5330 0.9933 -0.750 0.3248 0.01480 0.00760 -0.0365 0.5221 0.9988 -0.500 0.3510 0.01465 0.00733 -0.0366 0.5121 1.0000 -0.250 0.3733 0.01461 0.00719 -0.0359 0.5030 1.0000 0.000 0.3957 0.01459 0.00705 -0.0352 0.4949 1.0000 0.250 0.4184 0.01459 0.00698 -0.0346 0.4866 1.0000 0.500 0.4411 0.01460 0.00688 -0.0339 0.4797 1.0000 0.750 0.4639 0.01463 0.00685 -0.0332 0.4729 1.0000 1.000 0.4869 0.01466 0.00683 -0.0326 0.4664 1.0000 1.500 0.5332 0.01479 0.00685 -0.0314 0.4551 1.0000 1.750 0.5565 0.01486 0.00687 -0.0307 0.4499 1.0000 2.000 0.5798 0.01499 0.00690 -0.0301 0.4457 1.0000 2.250 0.6031 0.01507 0.00703 -0.0295 0.4407 1.0000 2.500 0.6266 0.01516 0.00712 -0.0289 0.4359 1.0000 2.750 0.6501 0.01528 0.00718 -0.0283 0.4317 1.0000 3.000 0.6735 0.01544 0.00734 -0.0277 0.4275 1.0000 3.250 0.6968 0.01557 0.00752 -0.0271 0.4229 1.0000 3.500 0.7202 0.01569 0.00764 -0.0265 0.4185 1.0000 3.750 0.7439 0.01586 0.00774 -0.0259 0.4147 1.0000 4.000 0.7670 0.01604 0.00801 -0.0253 0.4103 1.0000 4.250 0.7902 0.01619 0.00822 -0.0247 0.4056 1.0000 4.500 0.8136 0.01633 0.00835 -0.0241 0.4013 1.0000 4.750 0.8372 0.01658 0.00853 -0.0235 0.3975 1.0000 5.000 0.8597 0.01673 0.00885 -0.0227 0.3924 1.0000 5.250 0.8828 0.01688 0.00905 -0.0221 0.3876 1.0000 5.500 0.9064 0.01707 0.00918 -0.0215 0.3836 1.0000 5.750 0.9286 0.01729 0.00953 -0.0207 0.3784 1.0000 6.000 0.9512 0.01743 0.00975 -0.0199 0.3730 1.0000 6.250 0.9746 0.01762 0.00989 -0.0193 0.3688 1.0000 6.500 0.9964 0.01787 0.01029 -0.0184 0.3635 1.0000 6.750 1.0185 0.01804 0.01053 -0.0176 0.3580 1.0000 7.000 1.0419 0.01825 0.01067 -0.0170 0.3534 1.0000 7.250 1.0623 0.01851 0.01113 -0.0159 0.3472 1.0000 7.500 1.0844 0.01868 0.01134 -0.0151 0.3416 1.0000 7.750 1.1061 0.01897 0.01165 -0.0142 0.3358 1.0000 8.000 1.1261 0.01919 0.01203 -0.0131 0.3290 1.0000 8.250 1.1485 0.01943 0.01222 -0.0123 0.3234 1.0000 8.500 1.1668 0.01974 0.01274 -0.0109 0.3164 1.0000 8.750 1.1873 0.01993 0.01296 -0.0098 0.3098 1.0000 9.000 1.2060 0.02024 0.01340 -0.0085 0.3031 1.0000 9.250 1.2243 0.02040 0.01369 -0.0071 0.2956 1.0000 9.500 1.2422 0.02060 0.01398 -0.0056 0.2884 1.0000 9.750 1.2588 0.02069 0.01420 -0.0039 0.2800 1.0000 10.000 1.2745 0.02085 0.01453 -0.0020 0.2715 1.0000 10.250 1.2904 0.02092 0.01462 -0.0002 0.2632 1.0000 10.500 1.3034 0.02115 0.01502 0.0020 0.2528 1.0000 10.750 1.3151 0.02147 0.01543 0.0044 0.2421 1.0000 11.000 1.3245 0.02190 0.01592 0.0071 0.2314 1.0000 11.250 1.3304 0.02245 0.01648 0.0103 0.2206 1.0000 11.500 1.3335 0.02308 0.01718 0.0139 0.2091 1.0000 11.750 1.3330 0.02375 0.01794 0.0180 0.1980 1.0000 12.000 1.3258 0.02449 0.01871 0.0230 0.1885 1.0000 12.250 1.3082 0.02516 0.01939 0.0299 0.1820 1.0000 12.500 1.2919 0.02602 0.02031 0.0358 0.1750 1.0000 12.750 1.2740 0.02722 0.02151 0.0411 0.1683 1.0000 13.000 1.2601 0.02871 0.02306 0.0449 0.1606 1.0000 13.250 1.2453 0.03074 0.02505 0.0478 0.1535 1.0000 13.500 1.2356 0.03297 0.02735 0.0495 0.1449 1.0000 13.750 1.2238 0.03568 0.03006 0.0506 0.1374 1.0000 14.000 1.2130 0.03864 0.03306 0.0511 0.1297 1.0000 14.250 1.2027 0.04175 0.03621 0.0513 0.1228 1.0000 14.500 1.1904 0.04521 0.03968 0.0512 0.1161 1.0000 14.750 1.1801 0.04866 0.04318 0.0509 0.1094 1.0000 15.000 1.1681 0.05232 0.04683 0.0505 0.1037 1.0000 15.250 1.1582 0.05592 0.05050 0.0499 0.0979 1.0000 15.500 1.1482 0.05971 0.05430 0.0491 0.0926 1.0000 15.750 1.1393 0.06344 0.05806 0.0483 0.0873 1.0000 16.000 1.1307 0.06738 0.06205 0.0471 0.0822 1.0000 16.250 1.1234 0.07102 0.06565 0.0462 0.0774 1.0000 16.500 1.1157 0.07511 0.06986 0.0448 0.0728 1.0000 16.750 1.1105 0.07851 0.07314 0.0440 0.0680 1.0000 17.000 1.1033 0.08278 0.07758 0.0425 0.0644 1.0000 17.250 1.0969 0.08685 0.08169 0.0409 0.0607 1.0000 17.500 1.0932 0.09034 0.08516 0.0398 0.0569 1.0000 17.750 1.0871 0.09463 0.08958 0.0381 0.0536 1.0000