EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 100,000 Max Cl/Cd: 56.58 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e49-il-100000.txt Download as CSV file: xf-e49-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 49 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.000 -0.4053 0.10420 0.10019 -0.0175 1.0000 0.0431
-5.750 -0.4052 0.10066 0.09668 -0.0138 1.0000 0.0445
-5.500 -0.3990 0.09756 0.09360 -0.0139 1.0000 0.0462
-5.250 -0.3892 0.09449 0.09053 -0.0157 1.0000 0.0480
-5.000 -0.3750 0.09122 0.08726 -0.0190 1.0000 0.0504
-4.750 -0.3487 0.08776 0.08376 -0.0263 1.0000 0.0539
-4.500 -0.2919 0.08288 0.07872 -0.0439 1.0000 0.0566
-4.250 -0.3040 0.07978 0.07573 -0.0362 1.0000 0.0591
-4.000 -0.2871 0.07691 0.07285 -0.0379 1.0000 0.0637
-3.750 -0.2277 0.07192 0.06766 -0.0533 1.0000 0.0715
-3.500 -0.2202 0.06929 0.06504 -0.0514 1.0000 0.0749
-3.250 -0.1625 0.06513 0.06063 -0.0642 1.0000 0.0856
-3.000 -0.1513 0.06275 0.05830 -0.0630 1.0000 0.0910
-2.750 -0.0788 0.06018 0.05520 -0.0782 1.0000 0.1125
-2.500 -0.0740 0.05689 0.05216 -0.0755 1.0000 0.1162
-2.250 -0.0395 0.05478 0.04994 -0.0798 0.9991 0.1323
-1.750 0.0426 0.05169 0.04656 -0.0903 0.9947 0.2005
-0.750 0.2680 0.04331 0.03561 -0.1153 0.9864 0.0950
-0.500 0.3093 0.04286 0.03462 -0.1176 0.9846 0.0793
-0.250 0.3460 0.04254 0.03382 -0.1192 0.9776 0.0713
0.000 0.3884 0.04329 0.03431 -0.1219 0.9736 0.0703
0.250 0.4333 0.04256 0.03362 -0.1255 0.9570 0.0771
0.500 0.4900 0.04238 0.03331 -0.1305 0.9414 0.0811
0.750 0.5335 0.04233 0.03314 -0.1335 0.9301 0.0938
1.000 0.5699 0.04066 0.03338 -0.1353 0.9211 1.0000
1.250 0.6050 0.04099 0.03334 -0.1369 0.9106 1.0000
1.500 0.6418 0.04130 0.03344 -0.1389 0.9013 1.0000
1.750 0.6810 0.04151 0.03351 -0.1413 0.8927 1.0000
2.000 0.7123 0.04156 0.03347 -0.1424 0.8816 1.0000
2.250 0.7445 0.04157 0.03345 -0.1435 0.8708 1.0000
2.500 0.7784 0.04156 0.03341 -0.1449 0.8611 1.0000
2.750 0.8219 0.04135 0.03318 -0.1477 0.8545 1.0000
3.000 0.8511 0.04125 0.03310 -0.1482 0.8434 1.0000
3.250 0.8829 0.04105 0.03299 -0.1491 0.8330 1.0000
3.500 0.9303 0.04030 0.03231 -0.1522 0.8277 1.0000
3.750 0.9604 0.03985 0.03194 -0.1525 0.8159 1.0000
4.000 0.9930 0.03918 0.03139 -0.1530 0.8042 1.0000
4.250 1.0287 0.03819 0.03059 -0.1537 0.7925 1.0000
4.500 1.0675 0.03688 0.02944 -0.1546 0.7813 1.0000
4.750 1.1166 0.03490 0.02768 -0.1569 0.7745 1.0000
5.000 1.1508 0.03360 0.02659 -0.1570 0.7619 1.0000
5.250 1.1862 0.03210 0.02539 -0.1570 0.7496 1.0000
5.500 1.2259 0.03026 0.02383 -0.1575 0.7364 1.0000
5.750 1.2778 0.02751 0.02138 -0.1594 0.7181 1.0000
6.000 1.3384 0.02401 0.01781 -0.1614 0.6334 1.0000
6.250 1.3619 0.02407 0.01726 -0.1591 0.5102 1.0000
6.500 1.3561 0.02600 0.01817 -0.1528 0.3776 1.0000
6.750 1.3475 0.02838 0.01972 -0.1469 0.2621 1.0000
7.000 1.3333 0.03212 0.02196 -0.1410 0.0810 1.0000
7.250 1.3340 0.03495 0.02435 -0.1369 0.0455 1.0000
7.500 1.3419 0.03680 0.02640 -0.1338 0.0393 1.0000
7.750 1.3444 0.03909 0.02883 -0.1302 0.0362 1.0000
8.000 1.3485 0.04125 0.03117 -0.1268 0.0347 1.0000
8.250 1.3561 0.04332 0.03342 -0.1239 0.0335 1.0000
8.500 1.3697 0.04549 0.03571 -0.1218 0.0326 1.0000
8.750 1.3995 0.04782 0.03823 -0.1217 0.0318 1.0000
9.000 1.4594 0.05130 0.04197 -0.1254 0.0319 1.0000
9.250 1.4971 0.05519 0.04631 -0.1265 0.0314 1.0000
9.500 1.5125 0.05868 0.05024 -0.1247 0.0307 1.0000
9.750 1.5191 0.06237 0.05438 -0.1218 0.0305 1.0000
10.000 1.5191 0.06655 0.05904 -0.1182 0.0313 1.0000
10.250 1.5143 0.07099 0.06391 -0.1143 0.0324 1.0000
10.500 1.5055 0.07555 0.06884 -0.1105 0.0333 1.0000
10.750 1.4949 0.08056 0.07416 -0.1071 0.0342 1.0000
11.000 1.5027 0.08498 0.07884 -0.1052 0.0368 1.0000
11.250 1.4717 0.08835 0.08268 -0.0999 0.0377 1.0000
11.500 1.4398 0.09305 0.08780 -0.0961 0.0385 1.0000
11.750 1.4105 0.09843 0.09353 -0.0939 0.0393 1.0000
12.000 1.3834 0.10420 0.09958 -0.0932 0.0399 1.0000
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Polar data table (+)
Polar graphs
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