XFOIL Version 6.96 Calculated polar for: EPPLER 551 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7107 0.14466 0.14213 -0.0341 1.0000 0.0024 -19.500 -0.7350 0.13540 0.13276 -0.0387 1.0000 0.0023 -19.250 -0.7614 0.12601 0.12324 -0.0433 1.0000 0.0024 -19.000 -0.7641 0.12145 0.11862 -0.0455 1.0000 0.0023 -18.750 -0.7909 0.11245 0.10948 -0.0499 1.0000 0.0023 -18.500 -0.8009 0.10673 0.10368 -0.0526 1.0000 0.0022 -18.250 -0.8234 0.09901 0.09582 -0.0564 1.0000 0.0023 -18.000 -0.8299 0.09417 0.09090 -0.0586 1.0000 0.0022 -17.750 -0.8503 0.08727 0.08387 -0.0619 1.0000 0.0023 -17.500 -0.8604 0.08224 0.07874 -0.0641 1.0000 0.0022 -17.250 -0.8809 0.07584 0.07220 -0.0669 1.0000 0.0023 -17.000 -0.8808 0.07261 0.06891 -0.0682 1.0000 0.0023 -16.750 -0.8905 0.06813 0.06433 -0.0699 1.0000 0.0023 -16.500 -0.8938 0.06464 0.06075 -0.0711 1.0000 0.0023 -16.250 -0.9009 0.06079 0.05681 -0.0723 1.0000 0.0023 -16.000 -0.9028 0.05769 0.05363 -0.0732 1.0000 0.0023 -15.750 -0.8984 0.05540 0.05131 -0.0737 1.0000 0.0023 -15.500 -0.9032 0.05217 0.04799 -0.0744 1.0000 0.0023 -15.250 -0.9120 0.04863 0.04435 -0.0751 1.0000 0.0024 -15.000 -0.9123 0.04612 0.04176 -0.0753 1.0000 0.0024 -14.750 -0.9078 0.04420 0.03979 -0.0754 1.0000 0.0024 -14.500 -0.9127 0.04151 0.03704 -0.0752 1.0000 0.0025 -14.250 -0.9105 0.03959 0.03505 -0.0749 1.0000 0.0025 -14.000 -0.9081 0.03764 0.03306 -0.0747 0.9999 0.0026 -13.750 -0.8886 0.03551 0.03085 -0.0778 0.9984 0.0025 -13.500 -0.8745 0.03351 0.02881 -0.0796 0.9929 0.0027 -13.250 -0.8690 0.03179 0.02704 -0.0792 0.9795 0.0027 -13.000 -0.8426 0.02987 0.02506 -0.0831 0.9589 0.0027 -12.750 -0.7993 0.02793 0.02302 -0.0903 0.9463 0.0028 -12.500 -0.7457 0.02614 0.02115 -0.0993 0.9351 0.0031 -12.250 -0.6881 0.02441 0.01928 -0.1091 0.9153 0.0032 -12.000 -0.6578 0.02319 0.01786 -0.1127 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0.00171 -0.0934 0.5658 0.4540 -2.000 0.1862 0.00744 0.00169 -0.0935 0.5608 0.4557 -1.750 0.2152 0.00745 0.00167 -0.0938 0.5567 0.4574 -1.500 0.2439 0.00747 0.00166 -0.0941 0.5524 0.4589 -1.250 0.2724 0.00750 0.00165 -0.0942 0.5479 0.4603 -1.000 0.3007 0.00752 0.00165 -0.0944 0.5436 0.4626 -0.750 0.3295 0.00752 0.00165 -0.0947 0.5395 0.4647 -0.500 0.3580 0.00754 0.00166 -0.0949 0.5351 0.4666 -0.250 0.3862 0.00758 0.00168 -0.0950 0.5309 0.4685 0.000 0.4146 0.00762 0.00170 -0.0952 0.5271 0.4704 0.250 0.4433 0.00764 0.00172 -0.0954 0.5232 0.4723 0.500 0.4717 0.00768 0.00174 -0.0956 0.5189 0.4742 0.750 0.4998 0.00774 0.00177 -0.0957 0.5149 0.4758 1.000 0.5279 0.00778 0.00181 -0.0959 0.5110 0.4779 1.250 0.5564 0.00780 0.00184 -0.0961 0.5073 0.4803 1.500 0.5846 0.00784 0.00189 -0.0963 0.5032 0.4827 1.750 0.6123 0.00790 0.00194 -0.0964 0.4989 0.4850 2.000 0.6402 0.00795 0.00199 -0.0965 0.4950 0.4873 2.250 0.6684 0.00800 0.00205 -0.0966 0.4908 0.4895 2.500 0.6962 0.00806 0.00211 -0.0967 0.4860 0.4915 2.750 0.7234 0.00815 0.00218 -0.0967 0.4811 0.4934 3.000 0.7513 0.00819 0.00225 -0.0968 0.4765 0.4961 3.250 0.7788 0.00825 0.00233 -0.0969 0.4712 0.4990 3.500 0.8056 0.00834 0.00242 -0.0968 0.4654 0.5020 3.750 0.8331 0.00841 0.00250 -0.0969 0.4605 0.5051 4.000 0.8604 0.00849 0.00259 -0.0969 0.4551 0.5078 4.250 0.8867 0.00860 0.00269 -0.0967 0.4491 0.5101 4.500 0.9139 0.00867 0.00279 -0.0967 0.4440 0.5132 4.750 0.9403 0.00877 0.00291 -0.0966 0.4367 0.5164 5.000 0.9663 0.00888 0.00303 -0.0964 0.4297 0.5198 5.250 0.9924 0.00899 0.00315 -0.0962 0.4218 0.5231 5.500 1.0177 0.00914 0.00329 -0.0958 0.4135 0.5262 5.750 1.0426 0.00928 0.00344 -0.0955 0.4031 0.5299 6.000 1.0673 0.00944 0.00360 -0.0950 0.3924 0.5343 6.250 1.0905 0.00965 0.00379 -0.0943 0.3783 0.5387 6.500 1.1129 0.00990 0.00399 -0.0935 0.3632 0.5427 6.750 1.1337 0.01019 0.00424 -0.0924 0.3448 0.5467 7.000 1.1527 0.01054 0.00453 -0.0910 0.3248 0.5514 7.250 1.1703 0.01094 0.00485 -0.0894 0.3035 0.5561 7.500 1.1846 0.01135 0.00518 -0.0871 0.2818 0.5604 7.750 1.1961 0.01181 0.00556 -0.0843 0.2605 0.5652 8.000 1.2081 0.01230 0.00599 -0.0817 0.2398 0.5706 8.250 1.2188 0.01286 0.00646 -0.0789 0.2189 0.5761 8.500 1.2305 0.01338 0.00694 -0.0764 0.2024 0.5822 8.750 1.2403 0.01398 0.00748 -0.0736 0.1849 0.5891 9.250 1.2588 0.01527 0.00868 -0.0683 0.1534 0.6029 9.500 1.2679 0.01595 0.00934 -0.0658 0.1411 0.6103 9.750 1.2760 0.01672 0.01009 -0.0632 0.1286 0.6178 10.000 1.2854 0.01747 0.01084 -0.0610 0.1186 0.6263 10.250 1.2934 0.01833 0.01171 -0.0587 0.1082 0.6349 10.500 1.2997 0.01933 0.01270 -0.0564 0.0976 0.6444 10.750 1.3052 0.02043 0.01379 -0.0541 0.0875 0.6547 11.000 1.3112 0.02157 0.01494 -0.0521 0.0790 0.6678 11.250 1.3178 0.02273 0.01613 -0.0502 0.0711 0.6807 11.750 1.3288 0.02535 0.01882 -0.0467 0.0579 0.7133 12.000 1.3351 0.02667 0.02021 -0.0452 0.0522 0.7333 12.250 1.3401 0.02813 0.02174 -0.0437 0.0472 0.7575 12.500 1.3425 0.02978 0.02348 -0.0421 0.0412 0.7898 12.750 1.3455 0.03113 0.02506 -0.0402 0.0374 0.8643 13.000 1.3556 0.03272 0.02683 -0.0402 0.0334 1.0000 13.250 1.3588 0.03466 0.02878 -0.0391 0.0293 1.0000 13.500 1.3648 0.03642 0.03057 -0.0384 0.0268 1.0000 13.750 1.3689 0.03841 0.03258 -0.0376 0.0241 1.0000 14.000 1.3740 0.04037 0.03457 -0.0370 0.0219 1.0000 14.250 1.3785 0.04244 0.03666 -0.0364 0.0200 1.0000 14.500 1.3823 0.04461 0.03886 -0.0360 0.0177 1.0000 14.750 1.3865 0.04682 0.04111 -0.0356 0.0163 1.0000 15.000 1.3902 0.04913 0.04346 -0.0353 0.0146 1.0000 15.250 1.3947 0.05140 0.04577 -0.0352 0.0136 1.0000 15.500 1.3987 0.05377 0.04819 -0.0351 0.0125 1.0000 15.750 1.4011 0.05637 0.05083 -0.0350 0.0114 1.0000 16.000 1.4052 0.05883 0.05334 -0.0351 0.0104 1.0000 16.250 1.4073 0.06158 0.05613 -0.0353 0.0094 1.0000 16.500 1.4100 0.06430 0.05891 -0.0355 0.0087 1.0000 16.750 1.4124 0.06709 0.06174 -0.0358 0.0078 1.0000 17.000 1.4148 0.06996 0.06468 -0.0362 0.0076 1.0000 17.250 1.4158 0.07304 0.06782 -0.0368 0.0068 1.0000 17.500 1.4176 0.07608 0.07092 -0.0373 0.0063 1.0000 17.750 1.4178 0.07937 0.07427 -0.0381 0.0058 1.0000 18.000 1.4180 0.08270 0.07765 -0.0388 0.0053 1.0000 18.250 1.4187 0.08604 0.08107 -0.0397 0.0050 1.0000 18.500 1.4186 0.08954 0.08463 -0.0407 0.0046 1.0000 18.750 1.4182 0.09312 0.08828 -0.0418 0.0043 1.0000 19.000 1.4163 0.09696 0.09219 -0.0431 0.0041 1.0000 19.250 1.4157 0.10065 0.09596 -0.0443 0.0039 1.0000