XFOIL Version 6.96 Calculated polar for: EPPLER 549 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.2738 0.12914 0.12581 -0.0510 1.0000 0.0531 -13.750 -0.2696 0.12683 0.12351 -0.0511 1.0000 0.0542 -13.500 -0.4002 0.12508 0.12148 -0.0525 1.0000 0.0522 -13.250 -0.3907 0.12300 0.11941 -0.0517 1.0000 0.0531 -12.750 -0.3793 0.08505 0.08170 -0.0694 1.0000 0.0324 -12.500 -0.4058 0.07757 0.07416 -0.0723 1.0000 0.0317 -12.250 -0.4372 0.07036 0.06687 -0.0748 1.0000 0.0313 -12.000 -0.4651 0.06444 0.06087 -0.0760 1.0000 0.0308 -11.750 -0.5435 0.05394 0.04986 -0.0767 1.0000 0.0265 -11.500 -0.5639 0.05027 0.04614 -0.0750 1.0000 0.0262 -11.250 -0.5891 0.04815 0.04400 -0.0714 1.0000 0.0260 -11.000 -0.6108 0.04629 0.04212 -0.0685 0.9983 0.0257 -10.750 -0.7220 0.05725 0.05252 -0.0624 0.9970 0.0270 -10.500 -0.7034 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0.2063 0.01827 0.01133 -0.0615 0.6927 0.6841 -0.750 0.2310 0.01815 0.01120 -0.0613 0.6861 0.6859 -0.500 0.2581 0.01801 0.01100 -0.0616 0.6805 0.6881 -0.250 0.2873 0.01787 0.01074 -0.0623 0.6759 0.6907 0.000 0.3121 0.01768 0.01054 -0.0625 0.6692 0.6932 0.250 0.3410 0.01747 0.01022 -0.0635 0.6641 0.6956 0.500 0.3691 0.01741 0.01010 -0.0638 0.6598 0.6972 0.750 0.3935 0.01740 0.01014 -0.0634 0.6537 0.6990 1.000 0.4213 0.01734 0.01005 -0.0636 0.6486 0.7008 1.250 0.4496 0.01730 0.00996 -0.0640 0.6436 0.7026 1.500 0.4748 0.01725 0.00993 -0.0639 0.6372 0.7046 1.750 0.5040 0.01716 0.00978 -0.0646 0.6322 0.7069 2.000 0.5322 0.01716 0.00974 -0.0652 0.6277 0.7095 2.250 0.5581 0.01717 0.00977 -0.0654 0.6224 0.7120 2.500 0.5856 0.01717 0.00978 -0.0655 0.6181 0.7137 2.750 0.6156 0.01722 0.00979 -0.0662 0.6146 0.7156 3.000 0.6389 0.01731 0.00998 -0.0657 0.6090 0.7176 3.250 0.6660 0.01731 0.00999 -0.0659 0.6037 0.7199 3.500 0.6970 0.01731 0.00993 -0.0667 0.5994 0.7224 3.750 0.7211 0.01742 0.01013 -0.0666 0.5940 0.7253 4.000 0.7478 0.01749 0.01024 -0.0668 0.5892 0.7280 4.250 0.7767 0.01753 0.01028 -0.0671 0.5853 0.7302 4.500 0.8017 0.01765 0.01048 -0.0669 0.5801 0.7326 4.750 0.8266 0.01776 0.01068 -0.0667 0.5748 0.7353 5.000 0.8558 0.01782 0.01075 -0.0673 0.5707 0.7383 5.250 0.8834 0.01795 0.01090 -0.0676 0.5658 0.7415 5.500 0.9067 0.01800 0.01107 -0.0671 0.5591 0.7442 5.750 0.9367 0.01795 0.01099 -0.0675 0.5536 0.7470 6.000 0.9576 0.01806 0.01125 -0.0665 0.5463 0.7505 6.250 0.9853 0.01805 0.01127 -0.0667 0.5401 0.7544 6.500 1.0107 0.01814 0.01141 -0.0666 0.5334 0.7583 6.750 1.0342 0.01812 0.01149 -0.0659 0.5260 0.7613 7.000 1.0594 0.01815 0.01158 -0.0655 0.5191 0.7650 7.250 1.0820 0.01817 0.01171 -0.0648 0.5109 0.7693 7.500 1.1067 0.01821 0.01179 -0.0644 0.5030 0.7739 7.750 1.1284 0.01816 0.01185 -0.0634 0.4942 0.7778 8.000 1.1476 0.01821 0.01201 -0.0620 0.4846 0.7829 8.250 1.1718 0.01820 0.01201 -0.0615 0.4751 0.7889 8.500 1.1867 0.01821 0.01219 -0.0592 0.4639 0.7940 8.750 1.2026 0.01829 0.01238 -0.0573 0.4524 0.8004 9.000 1.2178 0.01835 0.01253 -0.0552 0.4399 0.8069 9.250 1.2300 0.01845 0.01272 -0.0526 0.4267 0.8141 9.500 1.2386 0.01859 0.01293 -0.0494 0.4124 0.8225 9.750 1.2429 0.01881 0.01323 -0.0455 0.3970 0.8322 10.000 1.2460 0.01916 0.01366 -0.0415 0.3804 0.8438 10.250 1.2479 0.01964 0.01420 -0.0377 0.3623 0.8584 10.500 1.2474 0.02026 0.01486 -0.0337 0.3430 0.8791 10.750 1.2452 0.02095 0.01565 -0.0297 0.3226 0.9239 11.000 1.2482 0.02218 0.01679 -0.0280 0.2993 1.0000 11.250 1.2474 0.02378 0.01824 -0.0259 0.2804 1.0000 11.500 1.2471 0.02544 0.01982 -0.0239 0.2627 1.0000 11.750 1.2469 0.02718 0.02152 -0.0220 0.2442 1.0000 12.000 1.2451 0.02909 0.02340 -0.0203 0.2248 1.0000 12.250 1.2406 0.03129 0.02552 -0.0186 0.2072 1.0000 12.500 1.2360 0.03365 0.02781 -0.0172 0.1903 1.0000 12.750 1.2314 0.03613 0.03023 -0.0159 0.1752 1.0000 13.000 1.2269 0.03872 0.03278 -0.0148 0.1611 1.0000 13.250 1.2225 0.04142 0.03544 -0.0140 0.1480 1.0000 13.500 1.2175 0.04428 0.03825 -0.0133 0.1359 1.0000 13.750 1.2144 0.04711 0.04106 -0.0128 0.1243 1.0000 14.000 1.2123 0.04995 0.04392 -0.0125 0.1134 1.0000 14.250 1.2096 0.05291 0.04689 -0.0123 0.1037 1.0000 14.500 1.2048 0.05618 0.05009 -0.0122 0.0955 1.0000 14.750 1.2039 0.05916 0.05312 -0.0123 0.0871 1.0000 15.000 1.2018 0.06232 0.05629 -0.0125 0.0799 1.0000 15.250 1.1989 0.06565 0.05961 -0.0128 0.0737 1.0000 15.500 1.1981 0.06883 0.06285 -0.0131 0.0675 1.0000 15.750 1.1957 0.07225 0.06625 -0.0137 0.0625 1.0000 16.000 1.1952 0.07547 0.06954 -0.0141 0.0577 1.0000 16.250 1.1945 0.07886 0.07299 -0.0149 0.0535 1.0000 16.500 1.1929 0.08222 0.07632 -0.0154 0.0496 1.0000 16.750 1.1935 0.08559 0.07984 -0.0163 0.0462 1.0000 17.000 1.1921 0.08920 0.08347 -0.0173 0.0431 1.0000 17.250 1.1925 0.09243 0.08672 -0.0179 0.0401 1.0000