XFOIL Version 6.96 Calculated polar for: EPPLER 1233 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.6142 0.07672 0.07354 -0.0724 1.0000 0.0151 -14.250 -0.6415 0.06919 0.06587 -0.0766 1.0000 0.0150 -14.000 -0.6595 0.06389 0.06046 -0.0790 1.0000 0.0149 -13.750 -0.6859 0.05818 0.05457 -0.0811 1.0000 0.0149 -13.500 -0.7061 0.05390 0.05016 -0.0818 1.0000 0.0148 -13.250 -0.7264 0.05014 0.04626 -0.0815 1.0000 0.0148 -13.000 -0.7476 0.04698 0.04292 -0.0804 1.0000 0.0149 -12.750 -0.7626 0.04461 0.04045 -0.0784 1.0000 0.0149 -12.500 -0.7559 0.04129 0.03691 -0.0818 0.9968 0.0150 -12.250 -0.7445 0.03825 0.03359 -0.0855 0.9933 0.0151 -12.000 -0.7302 0.03628 0.03142 -0.0877 0.9880 0.0152 -11.750 -0.7156 0.03309 0.02802 -0.0900 0.9845 0.0155 -11.500 -0.6936 0.03120 0.02605 -0.0917 0.9811 0.0158 -11.250 -0.6729 0.02967 0.02443 -0.0928 0.9755 0.0159 -11.000 -0.6449 0.02821 0.02289 -0.0950 0.9725 0.0162 -10.750 -0.6291 0.02691 0.02151 -0.0945 0.9644 0.0164 -10.500 -0.6013 0.02554 0.02004 -0.0961 0.9607 0.0166 -10.250 -0.5850 0.02441 0.01883 -0.0951 0.9510 0.0171 -10.000 -0.5618 0.02329 0.01761 -0.0952 0.9436 0.0176 -9.750 -0.5364 0.02216 0.01639 -0.0955 0.9364 0.0178 -9.500 -0.5155 0.02125 0.01537 -0.0947 0.9261 0.0181 -9.250 -0.4868 0.01984 0.01393 -0.0957 0.9199 0.0185 -9.000 -0.4600 0.01880 0.01289 -0.0963 0.9082 0.0192 -8.750 -0.4215 0.01785 0.01189 -0.0990 0.8990 0.0199 -8.500 -0.3719 0.01692 0.01087 -0.1038 0.8890 0.0212 -8.250 -0.3187 0.01580 0.00970 -0.1099 0.8746 0.0225 -8.000 -0.2610 0.01506 0.00884 -0.1166 0.8553 0.0244 -7.750 -0.2255 0.01449 0.00815 -0.1187 0.8297 0.0265 -7.500 -0.2004 0.01418 0.00769 -0.1185 0.8043 0.0284 -7.250 -0.1813 0.01381 0.00721 -0.1172 0.7814 0.0308 -7.000 -0.1628 0.01351 0.00680 -0.1156 0.7602 0.0341 -6.750 -0.1442 0.01323 0.00643 -0.1139 0.7415 0.0383 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0.3185 0.00960 0.00371 -0.0981 0.5118 0.6643 -1.500 0.3454 0.00970 0.00378 -0.0978 0.5042 0.6743 -1.250 0.3715 0.00985 0.00385 -0.0973 0.4968 0.6826 -1.000 0.3979 0.00999 0.00395 -0.0969 0.4902 0.6904 -0.750 0.4247 0.01012 0.00400 -0.0966 0.4830 0.6982 -0.500 0.4494 0.01030 0.00414 -0.0958 0.4762 0.7048 -0.250 0.4757 0.01046 0.00428 -0.0953 0.4699 0.7142 0.000 0.5005 0.01063 0.00444 -0.0945 0.4635 0.7225 0.250 0.5250 0.01087 0.00461 -0.0937 0.4575 0.7299 0.500 0.5521 0.01099 0.00469 -0.0935 0.4522 0.7360 0.750 0.5772 0.01105 0.00475 -0.0929 0.4466 0.7400 1.000 0.6018 0.01120 0.00483 -0.0922 0.4410 0.7434 1.250 0.6275 0.01130 0.00491 -0.0918 0.4360 0.7470 1.500 0.6531 0.01137 0.00496 -0.0914 0.4307 0.7506 1.750 0.6785 0.01149 0.00500 -0.0910 0.4256 0.7540 2.000 0.7036 0.01164 0.00508 -0.0906 0.4207 0.7570 2.250 0.7283 0.01167 0.00515 -0.0900 0.4167 0.7598 2.500 0.7529 0.01176 0.00523 -0.0894 0.4122 0.7627 2.750 0.7770 0.01189 0.00532 -0.0887 0.4077 0.7659 3.000 0.8017 0.01209 0.00545 -0.0883 0.4028 0.7694 3.250 0.8269 0.01216 0.00553 -0.0879 0.3992 0.7726 3.500 0.8516 0.01225 0.00561 -0.0874 0.3952 0.7753 3.750 0.8751 0.01237 0.00572 -0.0866 0.3913 0.7781 4.000 0.8985 0.01257 0.00588 -0.0859 0.3872 0.7811 4.250 0.9229 0.01272 0.00604 -0.0854 0.3837 0.7843 4.500 0.9471 0.01283 0.00617 -0.0848 0.3799 0.7875 4.750 0.9713 0.01298 0.00631 -0.0843 0.3762 0.7905 5.000 0.9951 0.01316 0.00646 -0.0838 0.3726 0.7933 5.250 1.0183 0.01340 0.00666 -0.0831 0.3688 0.7963 5.500 1.0414 0.01354 0.00685 -0.0824 0.3660 0.7993 5.750 1.0644 0.01368 0.00703 -0.0816 0.3628 0.8025 6.000 1.0873 0.01384 0.00720 -0.0809 0.3594 0.8057 6.250 1.1099 0.01405 0.00739 -0.0802 0.3560 0.8088 6.500 1.1328 0.01432 0.00762 -0.0796 0.3525 0.8119 6.750 1.1554 0.01452 0.00786 -0.0789 0.3497 0.8151 7.000 1.1772 0.01468 0.00808 -0.0780 0.3471 0.8184 7.250 1.1988 0.01487 0.00831 -0.0771 0.3442 0.8218 7.500 1.2201 0.01508 0.00853 -0.0762 0.3410 0.8254 8.250 1.2837 0.01588 0.00938 -0.0736 0.3323 0.8362 8.500 1.3039 0.01610 0.00967 -0.0726 0.3298 0.8402 8.750 1.3241 0.01635 0.00996 -0.0717 0.3271 0.8442 9.000 1.3434 0.01660 0.01024 -0.0705 0.3242 0.8483 9.250 1.3620 0.01689 0.01057 -0.0693 0.3214 0.8529 9.500 1.3828 0.01731 0.01096 -0.0686 0.3181 0.8579 9.750 1.4015 0.01761 0.01133 -0.0675 0.3160 0.8631 10.000 1.4188 0.01787 0.01170 -0.0661 0.3137 0.8684 10.250 1.4357 0.01818 0.01209 -0.0647 0.3111 0.8749 10.500 1.4524 0.01851 0.01248 -0.0633 0.3083 0.8822 10.750 1.4678 0.01887 0.01289 -0.0617 0.3057 0.8912 11.000 1.4844 0.01930 0.01334 -0.0604 0.3028 0.9016 11.250 1.4991 0.01967 0.01381 -0.0587 0.3003 0.9184 11.500 1.5169 0.01997 0.01428 -0.0580 0.2977 1.0000 11.750 1.5341 0.02049 0.01486 -0.0572 0.2947 1.0000 12.000 1.5499 0.02105 0.01545 -0.0563 0.2917 1.0000 12.250 1.5651 0.02168 0.01607 -0.0553 0.2885 1.0000 12.500 1.5820 0.02236 0.01672 -0.0545 0.2850 1.0000 12.750 1.5939 0.02306 0.01753 -0.0532 0.2825 1.0000 13.000 1.6065 0.02379 0.01834 -0.0520 0.2795 1.0000 13.250 1.6186 0.02457 0.01918 -0.0508 0.2765 1.0000 13.500 1.6300 0.02544 0.02007 -0.0496 0.2734 1.0000 13.750 1.6433 0.02633 0.02091 -0.0487 0.2697 1.0000 14.000 1.6523 0.02735 0.02206 -0.0474 0.2673 1.0000 14.250 1.6604 0.02847 0.02328 -0.0462 0.2637 1.0000 14.500 1.6670 0.02973 0.02458 -0.0450 0.2595 1.0000 14.750 1.6727 0.03113 0.02596 -0.0438 0.2552 1.0000 15.000 1.6787 0.03259 0.02754 -0.0428 0.2513 1.0000 15.250 1.6834 0.03421 0.02924 -0.0419 0.2464 1.0000 15.500 1.6862 0.03604 0.03108 -0.0410 0.2421 1.0000 15.750 1.6892 0.03792 0.03301 -0.0402 0.2380 1.0000 16.000 1.6941 0.03976 0.03496 -0.0397 0.2338 1.0000 16.250 1.6958 0.04190 0.03716 -0.0392 0.2294 1.0000 16.500 1.6942 0.04439 0.03966 -0.0386 0.2253 1.0000 16.750 1.6971 0.04660 0.04198 -0.0383 0.2212 1.0000 17.000 1.6961 0.04922 0.04467 -0.0381 0.2163 1.0000 17.250 1.6907 0.05233 0.04780 -0.0380 0.2117 1.0000 17.500 1.6891 0.05518 0.05075 -0.0380 0.2071 1.0000 17.750 1.6843 0.05845 0.05409 -0.0382 0.2019 1.0000 18.000 1.6731 0.06247 0.05812 -0.0384 0.1966 1.0000 18.250 1.6680 0.06597 0.06173 -0.0389 0.1912 1.0000 18.500 1.6563 0.07029 0.06610 -0.0395 0.1855 1.0000 18.750 1.6461 0.07452 0.07039 -0.0403 0.1803 1.0000 19.000 1.6332 0.07922 0.07516 -0.0413 0.1738 1.0000 19.250 1.6174 0.08434 0.08031 -0.0425 0.1680 1.0000