EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 50,000 Max Cl/Cd: 4.5 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e549-il-50000.txt Download as CSV file: xf-e549-il-50000.csv |
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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3165 0.10573 0.09968 -0.0545 1.0000 0.1430
-11.250 -0.4642 0.09276 0.08622 -0.0659 1.0000 0.1138
-11.000 -0.4759 0.08755 0.08106 -0.0668 1.0000 0.1109
-10.750 -0.5186 0.08104 0.07459 -0.0689 1.0000 0.1062
-10.500 -0.5778 0.07671 0.07026 -0.0683 1.0000 0.1039
-10.250 -0.6286 0.07529 0.06885 -0.0640 1.0000 0.1028
-10.000 -0.6749 0.07494 0.06852 -0.0576 1.0000 0.1023
-9.750 -0.7218 0.07463 0.06809 -0.0511 1.0000 0.1016
-9.500 -0.7247 0.07153 0.06499 -0.0485 1.0000 0.0999
-9.250 -0.7391 0.06914 0.06255 -0.0449 1.0000 0.0989
-9.000 -0.7552 0.06679 0.06011 -0.0413 1.0000 0.0977
-8.750 -0.7701 0.06435 0.05751 -0.0379 1.0000 0.0965
-8.500 -0.7829 0.06174 0.05467 -0.0346 1.0000 0.0951
-8.250 -0.7914 0.05899 0.05162 -0.0315 1.0000 0.0938
-8.000 -0.7955 0.05624 0.04852 -0.0288 1.0000 0.0926
-7.750 -0.7947 0.05364 0.04557 -0.0264 1.0000 0.0922
-7.500 -0.7895 0.05132 0.04296 -0.0243 1.0000 0.0932
-7.250 -0.7817 0.04917 0.04052 -0.0224 1.0000 0.0956
-7.000 -0.7712 0.04714 0.03813 -0.0205 1.0000 0.0978
-6.750 -0.7582 0.04521 0.03577 -0.0187 1.0000 0.1002
-6.500 -0.7408 0.04307 0.03350 -0.0172 1.0000 0.1033
-6.250 -0.7239 0.04161 0.03207 -0.0157 1.0000 0.1107
-6.000 -0.7041 0.04023 0.03067 -0.0139 1.0000 0.1192
-5.750 -0.6851 0.03920 0.02971 -0.0117 1.0000 0.1323
-5.500 -0.6699 0.03822 0.02897 -0.0091 1.0000 0.1503
-5.250 -0.6442 0.03661 0.02782 -0.0092 0.9932 0.1934
-5.000 -0.6414 0.03263 0.02542 -0.0085 0.9866 0.3048
-4.750 -0.6313 0.04341 0.03763 0.0119 0.9774 0.6409
-4.500 -0.3017 0.05971 0.05220 -0.0030 0.9709 0.8182
-4.250 -0.1733 0.05845 0.05034 -0.0184 0.9652 0.8916
-3.250 0.0349 0.05375 0.04462 -0.0475 0.9340 0.9673
-3.000 0.0697 0.05320 0.04389 -0.0519 0.9269 0.9684
-2.750 0.0639 0.05334 0.04399 -0.0487 0.9165 0.9618
-2.500 0.0622 0.05372 0.04430 -0.0461 0.9087 0.9556
-2.250 0.0691 0.05370 0.04422 -0.0451 0.9002 0.9537
-2.000 0.0833 0.05371 0.04414 -0.0453 0.8931 0.9529
-1.750 0.0815 0.05396 0.04435 -0.0427 0.8853 0.9511
-1.500 0.1030 0.05398 0.04427 -0.0440 0.8791 0.9510
-1.250 0.0809 0.05454 0.04484 -0.0379 0.8723 0.9480
-1.000 0.0931 0.05473 0.04495 -0.0376 0.8665 0.9479
-0.750 0.0867 0.05515 0.04535 -0.0342 0.8610 0.9469
-0.500 0.0712 0.05559 0.04578 -0.0293 0.8565 0.9458
-0.250 0.0727 0.05591 0.04606 -0.0272 0.8522 0.9458
0.000 0.0866 0.05626 0.04635 -0.0271 0.8477 0.9465
0.250 0.0670 0.05668 0.04677 -0.0218 0.8455 0.9466
0.500 0.0557 0.05707 0.04716 -0.0179 0.8446 0.9472
0.750 0.0477 0.05745 0.04753 -0.0145 0.8441 0.9484
1.000 0.0414 0.05784 0.04791 -0.0115 0.8446 0.9499
1.250 0.0391 0.05837 0.04842 -0.0093 0.8473 0.9515
1.500 -0.0180 0.05869 0.04883 0.0006 0.8788 0.9539
1.750 -0.2137 0.05310 0.04351 0.0363 1.0000 0.9607
2.000 -0.1980 0.05345 0.04382 0.0353 1.0000 0.9640
2.250 -0.1767 0.05414 0.04446 0.0332 0.9977 0.9679
2.500 -0.1408 0.05563 0.04589 0.0282 0.9901 0.9712
2.750 -0.1007 0.05744 0.04767 0.0222 0.9806 0.9743
3.000 -0.0638 0.05912 0.04932 0.0170 0.9687 0.9775
3.250 -0.0295 0.06059 0.05077 0.0124 0.9542 0.9811
3.500 0.0091 0.06241 0.05258 0.0070 0.9403 0.9849
3.750 0.0486 0.06442 0.05460 0.0015 0.9261 0.9894
4.000 0.0840 0.06622 0.05641 -0.0032 0.9118 0.9943
4.250 0.1102 0.06732 0.05754 -0.0063 0.8980 0.9995
4.500 0.1161 0.06767 0.05790 -0.0053 0.8851 1.0000
4.750 0.1209 0.06813 0.05836 -0.0041 0.8727 1.0000
5.000 0.1283 0.06883 0.05907 -0.0033 0.8609 1.0000
5.250 0.1428 0.07016 0.06040 -0.0037 0.8482 1.0000
5.500 0.1422 0.06995 0.06020 -0.0015 0.8343 1.0000
5.750 0.1455 0.07023 0.06048 -0.0004 0.8213 1.0000
6.000 0.1591 0.07140 0.06167 -0.0012 0.8085 1.0000
6.250 0.1806 0.07332 0.06359 -0.0034 0.7973 1.0000
6.500 0.2172 0.07648 0.06677 -0.0078 0.7854 1.0000
6.750 0.2338 0.07775 0.06807 -0.0092 0.7711 1.0000
7.000 0.2495 0.07923 0.06959 -0.0106 0.7575 1.0000
7.250 0.2672 0.08110 0.07149 -0.0124 0.7446 1.0000
7.500 0.2882 0.08334 0.07377 -0.0146 0.7324 1.0000
7.750 0.3177 0.08635 0.07684 -0.0179 0.7213 1.0000
8.000 0.3519 0.08960 0.08015 -0.0215 0.7075 1.0000
8.250 0.3613 0.09093 0.08152 -0.0221 0.6937 1.0000
8.500 0.3740 0.09286 0.08350 -0.0232 0.6804 1.0000
8.750 0.3892 0.09518 0.08587 -0.0246 0.6674 1.0000
9.000 0.4069 0.09779 0.08854 -0.0263 0.6549 1.0000
9.250 0.4304 0.10088 0.09170 -0.0284 0.6430 1.0000
9.500 0.4557 0.10402 0.09490 -0.0305 0.6290 1.0000
9.750 0.4789 0.10700 0.09797 -0.0322 0.6142 1.0000
10.000 0.4915 0.10927 0.10031 -0.0330 0.5995 1.0000
10.250 0.4979 0.11133 0.10243 -0.0335 0.5855 1.0000
10.500 0.5033 0.11370 0.10486 -0.0340 0.5729 1.0000
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Polar data table (+)
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