EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 100,000 Max Cl/Cd: 70.65 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e59-il-100000-n5.txt Download as CSV file: xf-e59-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 59 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4062 0.11867 0.11398 -0.0234 1.0000 0.0326
-7.750 -0.4106 0.11668 0.11205 -0.0222 1.0000 0.0326
-7.500 -0.4152 0.11459 0.11002 -0.0211 1.0000 0.0326
-7.250 -0.4158 0.11141 0.10692 -0.0207 1.0000 0.0327
-7.000 -0.4117 0.10642 0.10195 -0.0179 1.0000 0.0333
-6.750 -0.4091 0.10314 0.09869 -0.0162 1.0000 0.0337
-6.500 -0.4089 0.10058 0.09615 -0.0155 1.0000 0.0340
-6.250 -0.3967 0.09696 0.09254 -0.0179 0.9976 0.0346
-6.000 -0.3808 0.09335 0.08893 -0.0210 0.9945 0.0359
-5.750 -0.3632 0.08970 0.08527 -0.0254 0.9905 0.0374
-5.500 -0.3400 0.08576 0.08131 -0.0322 0.9866 0.0408
-5.250 -0.2897 0.08048 0.07594 -0.0524 0.9806 0.0436
-4.750 -0.2486 0.06928 0.06467 -0.0596 0.9743 0.0319
-4.500 -0.2286 0.06542 0.06078 -0.0621 0.9714 0.0299
-4.250 -0.1874 0.05962 0.05487 -0.0720 0.9693 0.0284
-4.000 -0.1373 0.05306 0.04810 -0.0840 0.9674 0.0277
-3.750 -0.0764 0.04586 0.04055 -0.0978 0.9664 0.0297
-3.500 0.0020 0.03700 0.03096 -0.1142 0.9686 0.0306
-3.250 0.0701 0.03023 0.02305 -0.1256 0.9703 0.0330
-3.000 0.1107 0.02866 0.02124 -0.1295 0.9690 0.0380
-2.750 0.1595 0.02598 0.01766 -0.1342 0.9686 0.0431
-2.500 0.1944 0.02473 0.01619 -0.1363 0.9657 0.0498
-2.250 0.2305 0.02381 0.01481 -0.1380 0.9628 0.0570
-2.000 0.2668 0.02280 0.01370 -0.1401 0.9606 0.0633
-1.750 0.3035 0.02211 0.01281 -0.1419 0.9584 0.0690
-1.500 0.3392 0.02158 0.01221 -0.1437 0.9563 0.0759
-1.250 0.3679 0.02130 0.01189 -0.1441 0.9514 0.0873
-1.000 0.4024 0.02096 0.01152 -0.1457 0.9480 0.0985
-0.750 0.4395 0.02066 0.01131 -0.1477 0.9453 0.1233
-0.500 0.4736 0.02037 0.01122 -0.1493 0.9418 0.1985
-0.250 0.5062 0.01978 0.01134 -0.1509 0.9370 0.4225
0.000 0.5323 0.01891 0.01143 -0.1500 0.9331 0.7697
0.500 0.5859 0.01882 0.01123 -0.1494 0.9208 1.0000
0.750 0.6203 0.01894 0.01124 -0.1508 0.9172 1.0000
1.000 0.6480 0.01909 0.01134 -0.1509 0.9109 1.0000
1.250 0.6794 0.01919 0.01139 -0.1516 0.9053 1.0000
1.500 0.7148 0.01916 0.01134 -0.1530 0.9002 1.0000
1.750 0.7443 0.01912 0.01131 -0.1531 0.8911 1.0000
2.000 0.7756 0.01899 0.01122 -0.1535 0.8817 1.0000
2.250 0.8139 0.01866 0.01094 -0.1551 0.8749 1.0000
2.500 0.8439 0.01842 0.01078 -0.1550 0.8629 1.0000
2.750 0.8807 0.01760 0.01003 -0.1555 0.8472 1.0000
3.000 0.9081 0.01706 0.00955 -0.1543 0.8224 1.0000
3.250 0.9384 0.01667 0.00927 -0.1539 0.7982 1.0000
3.500 0.9742 0.01626 0.00895 -0.1547 0.7761 1.0000
3.750 1.0178 0.01565 0.00835 -0.1565 0.7321 1.0000
4.000 1.0774 0.01525 0.00756 -0.1613 0.6165 1.0000
4.250 1.1072 0.01609 0.00777 -0.1611 0.5182 1.0000
4.500 1.1249 0.01716 0.00838 -0.1590 0.4069 1.0000
5.000 1.1552 0.01997 0.01007 -0.1548 0.2087 1.0000
5.250 1.1703 0.02161 0.01110 -0.1529 0.1081 1.0000
5.500 1.1882 0.02291 0.01222 -0.1512 0.0813 1.0000
5.750 1.2073 0.02397 0.01331 -0.1496 0.0698 1.0000
6.000 1.2264 0.02497 0.01444 -0.1480 0.0637 1.0000
6.250 1.2439 0.02616 0.01574 -0.1462 0.0598 1.0000
6.500 1.2623 0.02723 0.01705 -0.1444 0.0548 1.0000
6.750 1.2777 0.02868 0.01853 -0.1425 0.0488 1.0000
7.000 1.2958 0.02994 0.01997 -0.1408 0.0433 1.0000
7.250 1.3107 0.03188 0.02190 -0.1389 0.0384 1.0000
7.500 1.3308 0.03369 0.02395 -0.1375 0.0336 1.0000
7.750 1.3507 0.03589 0.02619 -0.1364 0.0294 1.0000
8.000 1.3743 0.03842 0.02898 -0.1357 0.0259 1.0000
8.250 1.3992 0.04127 0.03233 -0.1348 0.0232 1.0000
8.500 1.4170 0.04363 0.03503 -0.1332 0.0206 1.0000
8.750 1.4298 0.04573 0.03734 -0.1313 0.0187 1.0000
9.000 1.4422 0.04942 0.04130 -0.1295 0.0177 1.0000
9.250 1.4495 0.05363 0.04598 -0.1267 0.0172 1.0000
9.500 1.4514 0.05735 0.05023 -0.1231 0.0168 1.0000
9.750 1.4470 0.06111 0.05449 -0.1189 0.0165 1.0000
10.000 1.4365 0.06466 0.05848 -0.1141 0.0161 1.0000
10.250 1.4226 0.06839 0.06260 -0.1096 0.0157 1.0000
10.500 1.4063 0.07248 0.06705 -0.1057 0.0156 1.0000
10.750 1.3883 0.07682 0.07171 -0.1025 0.0154 1.0000
11.000 1.3686 0.08160 0.07680 -0.1003 0.0153 1.0000
11.250 1.3476 0.08691 0.08237 -0.0992 0.0154 1.0000
11.500 1.3256 0.09287 0.08857 -0.0994 0.0155 1.0000
11.750 1.3039 0.09935 0.09527 -0.1011 0.0156 1.0000
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Polar data table (+)
Polar graphs
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