XFOIL Version 6.96 Calculated polar for: EPPLER 553 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.5676 0.16823 0.16630 -0.0243 1.0000 0.0054 -18.750 -0.6558 0.14106 0.13882 -0.0362 1.0000 0.0050 -18.500 -0.6876 0.12975 0.12735 -0.0418 1.0000 0.0049 -18.250 -0.7130 0.12039 0.11784 -0.0464 1.0000 0.0049 -18.000 -0.7324 0.11264 0.10996 -0.0502 1.0000 0.0048 -17.750 -0.7502 0.10543 0.10262 -0.0537 1.0000 0.0048 -17.500 -0.7638 0.09929 0.09637 -0.0566 1.0000 0.0047 -17.250 -0.7805 0.09280 0.08974 -0.0596 1.0000 0.0048 -17.000 -0.7876 0.08809 0.08494 -0.0618 1.0000 0.0047 -16.750 -0.7986 0.08295 0.07968 -0.0640 1.0000 0.0047 -16.500 -0.8070 0.07835 0.07498 -0.0658 1.0000 0.0047 -16.250 -0.8132 0.07419 0.07072 -0.0675 1.0000 0.0047 -16.000 -0.8187 0.07028 0.06673 -0.0689 1.0000 0.0047 -15.750 -0.8236 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0.5248 4.000 0.8985 0.00852 0.00286 -0.1069 0.4684 0.5287 4.250 0.9250 0.00863 0.00296 -0.1067 0.4619 0.5327 4.500 0.9517 0.00873 0.00307 -0.1066 0.4557 0.5363 4.750 0.9786 0.00881 0.00317 -0.1065 0.4493 0.5406 5.000 1.0040 0.00895 0.00331 -0.1061 0.4428 0.5450 5.250 1.0313 0.00901 0.00342 -0.1061 0.4370 0.5496 5.500 1.0568 0.00916 0.00356 -0.1058 0.4298 0.5537 5.750 1.0829 0.00925 0.00369 -0.1056 0.4230 0.5592 6.000 1.1084 0.00938 0.00384 -0.1053 0.4157 0.5648 6.250 1.1335 0.00953 0.00400 -0.1049 0.4087 0.5701 6.500 1.1588 0.00964 0.00415 -0.1045 0.4010 0.5761 6.750 1.1831 0.00981 0.00433 -0.1040 0.3932 0.5825 7.000 1.2075 0.00996 0.00450 -0.1035 0.3845 0.5887 7.250 1.2312 0.01013 0.00470 -0.1029 0.3753 0.5960 7.500 1.2535 0.01035 0.00491 -0.1020 0.3652 0.6035 7.750 1.2765 0.01053 0.00513 -0.1012 0.3540 0.6122 8.250 1.3160 0.01104 0.00563 -0.0986 0.3284 0.6304 8.500 1.3326 0.01135 0.00592 -0.0967 0.3130 0.6401 8.750 1.3476 0.01174 0.00627 -0.0945 0.2949 0.6510 9.000 1.3611 0.01220 0.00669 -0.0922 0.2759 0.6627 9.250 1.3730 0.01273 0.00717 -0.0896 0.2567 0.6757 9.500 1.3844 0.01328 0.00768 -0.0870 0.2371 0.6901 9.750 1.3926 0.01395 0.00830 -0.0840 0.2160 0.7069 10.000 1.3995 0.01468 0.00898 -0.0809 0.1963 0.7257 10.250 1.4066 0.01542 0.00971 -0.0780 0.1782 0.7477 10.500 1.4132 0.01619 0.01049 -0.0751 0.1626 0.7749 10.750 1.4193 0.01698 0.01133 -0.0722 0.1491 0.8142 11.000 1.4218 0.01758 0.01220 -0.0687 0.1367 1.0000 11.250 1.4272 0.01866 0.01323 -0.0662 0.1237 1.0000 11.500 1.4320 0.01984 0.01436 -0.0638 0.1119 1.0000 12.000 1.4428 0.02235 0.01681 -0.0597 0.0924 1.0000 12.250 1.4469 0.02379 0.01823 -0.0577 0.0832 1.0000 12.500 1.4496 0.02539 0.01980 -0.0558 0.0746 1.0000 12.750 1.4525 0.02707 0.02145 -0.0542 0.0670 1.0000 13.000 1.4549 0.02885 0.02322 -0.0526 0.0593 1.0000 13.250 1.4570 0.03074 0.02510 -0.0512 0.0530 1.0000 13.500 1.4591 0.03271 0.02708 -0.0499 0.0480 1.0000 13.750 1.4635 0.03457 0.02897 -0.0490 0.0444 1.0000 14.000 1.4637 0.03685 0.03125 -0.0479 0.0396 1.0000 14.250 1.4670 0.03896 0.03339 -0.0472 0.0361 1.0000 14.500 1.4659 0.04154 0.03598 -0.0464 0.0320 1.0000 14.750 1.4696 0.04375 0.03823 -0.0459 0.0298 1.0000 15.000 1.4695 0.04640 0.04091 -0.0455 0.0271 1.0000 15.250 1.4718 0.04890 0.04345 -0.0452 0.0251 1.0000 15.500 1.4729 0.05159 0.04619 -0.0450 0.0232 1.0000 15.750 1.4724 0.05451 0.04915 -0.0449 0.0213 1.0000 16.000 1.4745 0.05723 0.05193 -0.0450 0.0198 1.0000 16.250 1.4740 0.06033 0.05507 -0.0452 0.0184 1.0000 16.500 1.4731 0.06353 0.05833 -0.0455 0.0173 1.0000 16.750 1.4743 0.06655 0.06142 -0.0459 0.0162 1.0000 17.000 1.4736 0.06987 0.06479 -0.0464 0.0152 1.0000 17.250 1.4707 0.07356 0.06853 -0.0470 0.0142 1.0000 17.500 1.4715 0.07681 0.07186 -0.0477 0.0136 1.0000 17.750 1.4705 0.08036 0.07548 -0.0486 0.0128 1.0000 18.000 1.4688 0.08406 0.07924 -0.0495 0.0121 1.0000 18.250 1.4646 0.08819 0.08343 -0.0507 0.0114 1.0000 18.500 1.4634 0.09197 0.08730 -0.0518 0.0109 1.0000 18.750 1.4621 0.09578 0.09118 -0.0531 0.0104 1.0000 19.000 1.4601 0.09973 0.09520 -0.0544 0.0099 1.0000 19.250 1.4557 0.10414 0.09968 -0.0560 0.0094 1.0000