XFOIL Version 6.96 Calculated polar for: NACA 2414 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -1.1513 0.08637 0.08297 -0.0417 1.0000 0.0159 -18.250 -1.2034 0.07478 0.07120 -0.0481 1.0000 0.0158 -18.000 -1.2484 0.06428 0.06051 -0.0541 1.0000 0.0157 -17.750 -1.2803 0.05571 0.05176 -0.0592 1.0000 0.0157 -17.500 -1.3010 0.04887 0.04476 -0.0636 1.0000 0.0158 -17.250 -1.3131 0.04353 0.03927 -0.0670 1.0000 0.0158 -17.000 -1.3192 0.03930 0.03491 -0.0696 1.0000 0.0159 -16.750 -1.3211 0.03592 0.03142 -0.0714 1.0000 0.0160 -16.500 -1.3213 0.03305 0.02844 -0.0725 1.0000 0.0161 -16.250 -1.3213 0.03053 0.02582 -0.0729 1.0000 0.0163 -16.000 -1.3186 0.02855 0.02375 -0.0726 1.0000 0.0165 -15.750 -1.3135 0.02697 0.02209 -0.0719 1.0000 0.0168 -15.500 -1.3068 0.02568 0.02074 -0.0707 1.0000 0.0170 -15.250 -1.2990 0.02460 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0.00145 -0.0511 0.5687 0.3098 -0.500 0.1871 0.00755 0.00143 -0.0510 0.5419 0.3529 -0.250 0.2147 0.00751 0.00143 -0.0509 0.5296 0.3775 0.000 0.2422 0.00748 0.00144 -0.0508 0.5171 0.4054 0.250 0.2696 0.00742 0.00145 -0.0506 0.5047 0.4399 0.500 0.2971 0.00736 0.00147 -0.0505 0.4936 0.4756 0.750 0.3245 0.00733 0.00150 -0.0504 0.4826 0.5113 1.000 0.3520 0.00729 0.00154 -0.0503 0.4717 0.5459 1.250 0.3795 0.00727 0.00158 -0.0502 0.4615 0.5780 1.500 0.4068 0.00728 0.00163 -0.0500 0.4504 0.6090 1.750 0.4343 0.00726 0.00169 -0.0499 0.4399 0.6410 2.000 0.4615 0.00727 0.00175 -0.0497 0.4283 0.6721 2.250 0.4883 0.00730 0.00183 -0.0494 0.4153 0.7038 2.500 0.5154 0.00731 0.00190 -0.0492 0.4026 0.7353 2.750 0.5421 0.00734 0.00199 -0.0489 0.3900 0.7675 3.000 0.5683 0.00739 0.00209 -0.0484 0.3764 0.8003 3.250 0.5943 0.00746 0.00220 -0.0479 0.3613 0.8313 3.500 0.6197 0.00755 0.00233 -0.0473 0.3456 0.8621 3.750 0.6447 0.00768 0.00246 -0.0466 0.3278 0.8900 4.000 0.6696 0.00784 0.00261 -0.0459 0.3098 0.9157 4.500 0.7222 0.00825 0.00293 -0.0451 0.2738 0.9565 4.750 0.7531 0.00854 0.00313 -0.0458 0.2522 0.9735 5.000 0.7854 0.00885 0.00333 -0.0468 0.2321 0.9844 5.250 0.8170 0.00913 0.00353 -0.0478 0.2139 0.9904 5.500 0.8478 0.00943 0.00374 -0.0486 0.1959 0.9942 5.750 0.8797 0.00977 0.00397 -0.0497 0.1766 0.9968 6.000 0.9105 0.01014 0.00423 -0.0506 0.1574 0.9997 6.250 0.9324 0.01045 0.00446 -0.0495 0.1424 1.0000 6.500 0.9533 0.01075 0.00469 -0.0482 0.1297 1.0000 6.750 0.9748 0.01104 0.00492 -0.0470 0.1187 1.0000 7.000 0.9969 0.01133 0.00517 -0.0459 0.1088 1.0000 7.250 1.0190 0.01166 0.00543 -0.0449 0.0990 1.0000 7.500 1.0412 0.01199 0.00571 -0.0440 0.0902 1.0000 7.750 1.0636 0.01232 0.00600 -0.0430 0.0825 1.0000 8.000 1.0863 0.01264 0.00629 -0.0422 0.0758 1.0000 8.250 1.1086 0.01299 0.00660 -0.0413 0.0697 1.0000 8.500 1.1307 0.01334 0.00693 -0.0404 0.0641 1.0000 8.750 1.1529 0.01368 0.00725 -0.0395 0.0594 1.0000 9.000 1.1744 0.01407 0.00761 -0.0385 0.0548 1.0000 9.250 1.1961 0.01442 0.00795 -0.0375 0.0511 1.0000 9.500 1.2171 0.01481 0.00833 -0.0365 0.0478 1.0000 9.750 1.2379 0.01519 0.00870 -0.0354 0.0448 1.0000 10.000 1.2576 0.01561 0.00912 -0.0342 0.0421 1.0000 10.250 1.2764 0.01599 0.00950 -0.0327 0.0399 1.0000 10.500 1.2938 0.01643 0.00994 -0.0311 0.0378 1.0000 10.750 1.3114 0.01687 0.01040 -0.0296 0.0362 1.0000 11.000 1.3289 0.01733 0.01087 -0.0281 0.0345 1.0000 11.250 1.3453 0.01786 0.01141 -0.0265 0.0328 1.0000 11.500 1.3619 0.01839 0.01196 -0.0250 0.0314 1.0000 11.750 1.3783 0.01894 0.01254 -0.0235 0.0300 1.0000 12.000 1.3935 0.01957 0.01319 -0.0220 0.0287 1.0000 12.250 1.4083 0.02025 0.01388 -0.0204 0.0276 1.0000 12.500 1.4236 0.02091 0.01458 -0.0191 0.0267 1.0000 12.750 1.4379 0.02165 0.01535 -0.0176 0.0258 1.0000 13.000 1.4510 0.02248 0.01621 -0.0162 0.0249 1.0000 13.250 1.4631 0.02341 0.01717 -0.0147 0.0240 1.0000 13.500 1.4762 0.02430 0.01812 -0.0135 0.0234 1.0000 13.750 1.4884 0.02528 0.01914 -0.0122 0.0227 1.0000 14.000 1.4995 0.02639 0.02029 -0.0110 0.0219 1.0000 14.250 1.5094 0.02762 0.02156 -0.0098 0.0212 1.0000 14.500 1.5179 0.02900 0.02298 -0.0087 0.0206 1.0000 14.750 1.5274 0.03035 0.02440 -0.0077 0.0201 1.0000 15.000 1.5361 0.03182 0.02593 -0.0069 0.0196 1.0000 15.250 1.5437 0.03343 0.02760 -0.0061 0.0192 1.0000 15.500 1.5501 0.03520 0.02943 -0.0054 0.0187 1.0000 15.750 1.5552 0.03716 0.03145 -0.0048 0.0183 1.0000 16.000 1.5590 0.03932 0.03367 -0.0043 0.0178 1.0000 16.250 1.5610 0.04171 0.03612 -0.0039 0.0174 1.0000 16.500 1.5637 0.04411 0.03861 -0.0038 0.0172 1.0000 16.750 1.5661 0.04663 0.04121 -0.0037 0.0169 1.0000 17.000 1.5671 0.04937 0.04404 -0.0038 0.0166 1.0000 17.250 1.5666 0.05235 0.04710 -0.0041 0.0164 1.0000 17.500 1.5649 0.05557 0.05039 -0.0045 0.0161 1.0000 17.750 1.5620 0.05900 0.05391 -0.0051 0.0158 1.0000 18.000 1.5577 0.06265 0.05765 -0.0058 0.0156 1.0000 18.250 1.5517 0.06659 0.06168 -0.0067 0.0154 1.0000 18.500 1.5442 0.07083 0.06601 -0.0077 0.0151 1.0000 18.750 1.5353 0.07534 0.07061 -0.0090 0.0149 1.0000 19.000 1.5245 0.08014 0.07550 -0.0104 0.0147 1.0000 19.250 1.5127 0.08519 0.08065 -0.0120 0.0146 1.0000