XFOIL Version 6.96 Calculated polar for: EPPLER 540 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4759 0.01966 0.01422 -0.1001 0.8517 0.0046 -9.250 -0.4569 0.01890 0.01331 -0.0989 0.8427 0.0045 -9.000 -0.4386 0.01811 0.01241 -0.0977 0.8341 0.0044 -8.750 -0.4206 0.01758 0.01180 -0.0965 0.8263 0.0044 -8.500 -0.4057 0.01672 0.01083 -0.0947 0.8187 0.0044 -8.250 -0.3918 0.01599 0.01000 -0.0929 0.8119 0.0045 -8.000 -0.3745 0.01556 0.00951 -0.0916 0.8053 0.0044 -7.750 -0.3612 0.01491 0.00878 -0.0896 0.7994 0.0045 -7.500 -0.3484 0.01424 0.00804 -0.0875 0.7937 0.0048 -7.250 -0.3337 0.01374 0.00746 -0.0857 0.7883 0.0051 -7.000 -0.3170 0.01334 0.00702 -0.0842 0.7835 0.0052 -6.750 -0.3007 0.01293 0.00657 -0.0827 0.7784 0.0055 -6.500 -0.2842 0.01256 0.00614 -0.0811 0.7738 0.0058 -6.250 -0.2694 0.01212 0.00564 -0.0792 0.7695 0.0073 -6.000 -0.2554 0.01168 0.00519 -0.0771 0.7652 0.0096 -5.750 -0.2448 0.01120 0.00473 -0.0744 0.7611 0.0191 -5.500 -0.2364 0.01084 0.00441 -0.0712 0.7571 0.0339 -5.250 -0.2253 0.01050 0.00415 -0.0685 0.7533 0.0534 -5.000 -0.2103 0.01015 0.00390 -0.0665 0.7496 0.0800 -4.750 -0.1963 0.00973 0.00363 -0.0644 0.7461 0.1231 -4.500 -0.1817 0.00927 0.00336 -0.0625 0.7429 0.1783 -4.250 -0.1789 0.00814 0.00286 -0.0588 0.7396 0.3282 -4.000 -0.1788 0.00641 0.00207 -0.0549 0.7362 0.5660 -3.750 -0.1558 0.00620 0.00217 -0.0542 0.7333 0.6719 -3.500 -0.1269 0.00634 0.00225 -0.0545 0.7306 0.6877 -3.250 -0.0980 0.00646 0.00233 -0.0548 0.7281 0.6954 -3.000 -0.0691 0.00660 0.00243 -0.0552 0.7257 0.7033 -2.750 -0.0402 0.00676 0.00258 -0.0554 0.7231 0.7094 -2.500 -0.0112 0.00703 0.00282 -0.0557 0.7206 0.7172 -2.250 0.0179 0.00736 0.00318 -0.0557 0.7182 0.7242 -2.000 0.0475 0.00769 0.00348 -0.0561 0.7157 0.7300 -1.750 0.0763 0.00772 0.00346 -0.0565 0.7135 0.7317 -1.500 0.1051 0.00770 0.00341 -0.0570 0.7111 0.7325 -1.250 0.1336 0.00761 0.00330 -0.0575 0.7086 0.7335 -1.000 0.1622 0.00756 0.00322 -0.0579 0.7062 0.7342 -0.750 0.1911 0.00753 0.00316 -0.0584 0.7037 0.7349 -0.500 0.2203 0.00756 0.00314 -0.0590 0.7009 0.7356 -0.250 0.2485 0.00752 0.00312 -0.0593 0.6983 0.7363 0.000 0.2768 0.00750 0.00309 -0.0597 0.6952 0.7369 0.250 0.3053 0.00748 0.00305 -0.0601 0.6920 0.7376 0.500 0.3340 0.00748 0.00303 -0.0605 0.6889 0.7382 0.750 0.3626 0.00749 0.00302 -0.0610 0.6857 0.7389 1.000 0.3906 0.00747 0.00301 -0.0613 0.6823 0.7397 1.250 0.4187 0.00745 0.00300 -0.0616 0.6786 0.7405 1.500 0.4470 0.00746 0.00298 -0.0620 0.6749 0.7413 1.750 0.4753 0.00747 0.00298 -0.0624 0.6712 0.7420 2.000 0.5031 0.00744 0.00297 -0.0626 0.6673 0.7428 2.250 0.5309 0.00743 0.00297 -0.0629 0.6631 0.7435 2.500 0.5591 0.00747 0.00297 -0.0633 0.6588 0.7442 2.750 0.5865 0.00745 0.00298 -0.0635 0.6544 0.7449 3.000 0.6140 0.00744 0.00299 -0.0637 0.6494 0.7455 3.250 0.6415 0.00749 0.00301 -0.0639 0.6444 0.7461 3.500 0.6687 0.00747 0.00304 -0.0640 0.6388 0.7467 3.750 0.6954 0.00746 0.00304 -0.0641 0.6325 0.7475 4.000 0.7221 0.00744 0.00305 -0.0641 0.6257 0.7484 4.250 0.7481 0.00746 0.00307 -0.0640 0.6179 0.7491 4.500 0.7743 0.00747 0.00312 -0.0639 0.6087 0.7497 4.750 0.7993 0.00751 0.00317 -0.0636 0.5970 0.7504 5.000 0.8235 0.00758 0.00324 -0.0631 0.5824 0.7511 5.250 0.8462 0.00769 0.00332 -0.0623 0.5635 0.7519 5.500 0.8661 0.00789 0.00344 -0.0609 0.5362 0.7527 5.750 0.8819 0.00821 0.00362 -0.0588 0.4998 0.7535 6.000 0.8935 0.00867 0.00390 -0.0559 0.4552 0.7544 6.250 0.9020 0.00917 0.00421 -0.0524 0.4100 0.7554 6.500 0.9080 0.00966 0.00451 -0.0484 0.3684 0.7565 6.750 0.9143 0.01021 0.00488 -0.0446 0.3286 0.7576 7.000 0.9239 0.01073 0.00526 -0.0415 0.2955 0.7587 7.250 0.9331 0.01129 0.00567 -0.0385 0.2639 0.7596 7.750 0.9506 0.01249 0.00660 -0.0325 0.2057 0.7611 8.000 0.9607 0.01303 0.00707 -0.0299 0.1817 0.7622 8.250 0.9702 0.01363 0.00758 -0.0272 0.1594 0.7633 8.500 0.9797 0.01428 0.00815 -0.0247 0.1388 0.7643 8.750 0.9892 0.01496 0.00876 -0.0223 0.1191 0.7653 9.000 0.9977 0.01573 0.00944 -0.0198 0.0995 0.7663 9.250 1.0065 0.01653 0.01015 -0.0175 0.0815 0.7674 9.500 1.0155 0.01737 0.01091 -0.0153 0.0653 0.7684 9.750 1.0267 0.01812 0.01163 -0.0135 0.0547 0.7695 10.000 1.0372 0.01896 0.01242 -0.0117 0.0441 0.7707 10.250 1.0478 0.01981 0.01325 -0.0100 0.0357 0.7719 10.500 1.0581 0.02071 0.01412 -0.0083 0.0286 0.7730 10.750 1.0714 0.02147 0.01490 -0.0071 0.0250 0.7739 11.000 1.0831 0.02235 0.01577 -0.0057 0.0218 0.7748 11.250 1.0944 0.02326 0.01670 -0.0043 0.0185 0.7757 11.500 1.1079 0.02403 0.01752 -0.0032 0.0170 0.7770 11.750 1.1190 0.02497 0.01847 -0.0020 0.0147 0.7782 12.000 1.1287 0.02605 0.01959 -0.0006 0.0125 0.7794 12.250 1.1423 0.02688 0.02047 0.0003 0.0113 0.7805 12.500 1.1517 0.02802 0.02163 0.0016 0.0092 0.7817 12.750 1.1607 0.02924 0.02291 0.0028 0.0074 0.7829 13.000 1.1699 0.03045 0.02413 0.0039 0.0061 0.7841 13.250 1.1753 0.03200 0.02575 0.0053 0.0048 0.7853 13.500 1.1848 0.03328 0.02709 0.0062 0.0044 0.7865 13.750 1.1938 0.03463 0.02849 0.0071 0.0041 0.7877 14.000 1.2018 0.03609 0.03001 0.0080 0.0038 0.7888 14.250 1.2084 0.03769 0.03167 0.0088 0.0035 0.7902 14.500 1.2064 0.04011 0.03422 0.0102 0.0030 0.7918 14.750 1.2133 0.04180 0.03601 0.0108 0.0027 0.7933 15.000 1.2210 0.04344 0.03772 0.0113 0.0025 0.7947 15.250 1.2243 0.04556 0.03994 0.0119 0.0024 0.7961 15.500 1.2299 0.04752 0.04199 0.0123 0.0024 0.7975 15.750 1.2329 0.04980 0.04437 0.0126 0.0024 0.7990 16.000 1.2362 0.05213 0.04678 0.0128 0.0022 0.8004 16.250 1.2373 0.05476 0.04951 0.0129 0.0022 0.8017 16.500 1.2372 0.05762 0.05246 0.0129 0.0021 0.8030 16.750 1.2352 0.06078 0.05573 0.0127 0.0020 0.8045 17.000 1.2366 0.06363 0.05868 0.0123 0.0020 0.8062 17.250 1.2251 0.06824 0.06344 0.0116 0.0019 0.8076 17.500 1.2178 0.07247 0.06781 0.0107 0.0019 0.8091 17.750 1.2123 0.07666 0.07212 0.0095 0.0019 0.8106 18.000 1.2012 0.08183 0.07744 0.0079 0.0018 0.8120 18.250 1.1908 0.08707 0.08283 0.0059 0.0018 0.8134 18.500 1.1757 0.09329 0.08920 0.0034 0.0018 0.8146 18.750 1.1620 0.09952 0.09557 0.0007 0.0018 0.8158