XFOIL Version 6.96 Calculated polar for: EPPLER 603 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.6378 0.10032 0.09806 -0.0686 1.0000 0.0087 -17.000 -0.6649 0.09053 0.08810 -0.0742 1.0000 0.0086 -16.750 -0.6915 0.08143 0.07884 -0.0797 1.0000 0.0086 -16.500 -0.7025 0.07558 0.07289 -0.0831 1.0000 0.0085 -16.250 -0.7009 0.07210 0.06936 -0.0852 1.0000 0.0085 -16.000 -0.7429 0.06232 0.05932 -0.0902 1.0000 0.0085 -15.750 -0.7271 0.06140 0.05842 -0.0907 1.0000 0.0085 -15.500 -0.7651 0.05211 0.04880 -0.0958 0.9985 0.0086 -15.250 -0.7617 0.04810 0.04464 -0.0990 0.9792 0.0085 -15.000 -0.7339 0.04092 0.03710 -0.1126 0.9416 0.0087 -14.750 -0.6959 0.03704 0.03260 -0.1227 0.8418 0.0089 -14.500 -0.6986 0.03537 0.03066 -0.1210 0.8005 0.0089 -14.250 -0.6973 0.03385 0.02896 -0.1197 0.7776 0.0090 -14.000 -0.6932 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0.7238 0.250 0.4725 0.00838 0.00360 -0.0902 0.5924 0.7252 0.500 0.5024 0.00846 0.00363 -0.0909 0.5902 0.7264 0.750 0.5323 0.00851 0.00366 -0.0916 0.5886 0.7273 1.000 0.5619 0.00851 0.00366 -0.0921 0.5871 0.7281 1.250 0.5914 0.00848 0.00363 -0.0927 0.5854 0.7292 1.500 0.6206 0.00843 0.00360 -0.0932 0.5835 0.7306 1.750 0.6498 0.00843 0.00360 -0.0937 0.5815 0.7316 2.000 0.6790 0.00843 0.00360 -0.0942 0.5795 0.7325 2.250 0.7081 0.00845 0.00361 -0.0947 0.5774 0.7333 2.500 0.7373 0.00850 0.00365 -0.0952 0.5750 0.7342 2.750 0.7665 0.00858 0.00373 -0.0958 0.5726 0.7352 3.000 0.7952 0.00858 0.00376 -0.0962 0.5706 0.7363 3.250 0.8239 0.00858 0.00378 -0.0966 0.5682 0.7374 3.500 0.8527 0.00857 0.00380 -0.0970 0.5653 0.7384 3.750 0.8813 0.00858 0.00380 -0.0975 0.5623 0.7394 4.000 0.9098 0.00863 0.00383 -0.0979 0.5589 0.7404 4.250 0.9384 0.00867 0.00388 -0.0983 0.5558 0.7414 4.500 0.9667 0.00866 0.00392 -0.0987 0.5526 0.7424 4.750 0.9950 0.00867 0.00395 -0.0990 0.5490 0.7434 5.000 1.0230 0.00871 0.00398 -0.0993 0.5452 0.7443 5.250 1.0506 0.00879 0.00405 -0.0996 0.5411 0.7450 5.500 1.0787 0.00879 0.00410 -0.0999 0.5369 0.7457 5.750 1.1063 0.00877 0.00411 -0.1002 0.5320 0.7469 6.000 1.1327 0.00882 0.00416 -0.1002 0.5269 0.7480 6.250 1.1601 0.00885 0.00424 -0.1005 0.5214 0.7489 6.500 1.1865 0.00891 0.00432 -0.1005 0.5148 0.7499 6.750 1.2122 0.00900 0.00443 -0.1004 0.5077 0.7509 7.000 1.2372 0.00910 0.00454 -0.1002 0.4985 0.7520 7.250 1.2620 0.00922 0.00468 -0.0999 0.4888 0.7531 7.500 1.2849 0.00940 0.00484 -0.0993 0.4777 0.7542 7.750 1.3063 0.00962 0.00503 -0.0984 0.4642 0.7553 8.000 1.3262 0.00989 0.00526 -0.0973 0.4496 0.7564 8.250 1.3443 0.01020 0.00553 -0.0959 0.4330 0.7575 8.500 1.3586 0.01056 0.00583 -0.0938 0.4148 0.7586 8.750 1.3687 0.01096 0.00617 -0.0908 0.3961 0.7597 9.000 1.3768 0.01150 0.00663 -0.0876 0.3759 0.7608 9.250 1.3841 0.01211 0.00717 -0.0845 0.3573 0.7618 9.500 1.3904 0.01276 0.00775 -0.0813 0.3387 0.7633 9.750 1.3944 0.01351 0.00844 -0.0779 0.3188 0.7649 10.000 1.3945 0.01448 0.00934 -0.0741 0.2979 0.7663 10.500 1.3887 0.01707 0.01179 -0.0668 0.2576 0.7690 10.750 1.3876 0.01854 0.01320 -0.0639 0.2409 0.7704 11.000 1.3868 0.02014 0.01476 -0.0614 0.2252 0.7718 11.250 1.3858 0.02187 0.01644 -0.0590 0.2099 0.7732 11.500 1.3848 0.02371 0.01823 -0.0569 0.1950 0.7746 11.750 1.3845 0.02557 0.02004 -0.0550 0.1811 0.7758 12.000 1.3843 0.02749 0.02192 -0.0532 0.1680 0.7771 12.250 1.3853 0.02938 0.02378 -0.0517 0.1568 0.7781 12.500 1.3875 0.03121 0.02559 -0.0503 0.1462 0.7795 12.750 1.3899 0.03308 0.02745 -0.0490 0.1357 0.7811 13.000 1.3925 0.03498 0.02934 -0.0479 0.1264 0.7826 13.250 1.3941 0.03701 0.03134 -0.0468 0.1165 0.7840 13.500 1.3982 0.03892 0.03325 -0.0459 0.1080 0.7853 13.750 1.4021 0.04089 0.03520 -0.0451 0.0996 0.7866 14.000 1.4036 0.04312 0.03741 -0.0442 0.0907 0.7880 14.250 1.4092 0.04503 0.03932 -0.0437 0.0840 0.7894 14.500 1.4128 0.04719 0.04148 -0.0431 0.0772 0.7907 14.750 1.4169 0.04934 0.04362 -0.0427 0.0706 0.7921 15.000 1.4218 0.05146 0.04576 -0.0423 0.0653 0.7933 15.250 1.4250 0.05378 0.04805 -0.0420 0.0591 0.7944 15.500 1.4300 0.05600 0.05030 -0.0418 0.0544 0.7958 15.750 1.4333 0.05839 0.05270 -0.0416 0.0493 0.7976 16.000 1.4371 0.06080 0.05513 -0.0415 0.0448 0.7993 16.250 1.4407 0.06326 0.05761 -0.0415 0.0407 0.8010 16.500 1.4431 0.06590 0.06028 -0.0415 0.0365 0.8028 16.750 1.4463 0.06853 0.06293 -0.0416 0.0327 0.8046 17.000 1.4472 0.07147 0.06589 -0.0418 0.0289 0.8063 17.250 1.4486 0.07441 0.06884 -0.0421 0.0253 0.8079 17.500 1.4500 0.07739 0.07186 -0.0425 0.0224 0.8095 17.750 1.4498 0.08065 0.07515 -0.0430 0.0198 0.8109 18.000 1.4514 0.08375 0.07830 -0.0435 0.0181 0.8128 18.250 1.4508 0.08715 0.08175 -0.0442 0.0165 0.8148 18.500 1.4521 0.09036 0.08504 -0.0450 0.0154 0.8168 18.750 1.4527 0.09368 0.08842 -0.0458 0.0144 0.8188