EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 200,000 Max Cl/Cd: 103.63 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e59-il-200000.txt Download as CSV file: xf-e59-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.750 -0.4154 0.08668 0.08362 -0.0238 1.0000 0.0335
-5.500 -0.4183 0.08423 0.08120 -0.0175 1.0000 0.0348
-5.250 -0.4119 0.08160 0.07857 -0.0174 1.0000 0.0360
-5.000 -0.4014 0.07847 0.07544 -0.0196 1.0000 0.0373
-4.750 -0.3863 0.07488 0.07185 -0.0233 1.0000 0.0388
-4.500 -0.3570 0.07033 0.06725 -0.0312 0.9991 0.0413
-4.250 -0.2492 0.06103 0.05752 -0.0625 0.9952 0.0445
-4.000 -0.2343 0.05517 0.05176 -0.0641 0.9921 0.0465
-3.750 -0.2015 0.05206 0.04860 -0.0682 0.9886 0.0494
-3.500 -0.1147 0.04323 0.03917 -0.0885 0.9882 0.0590
-3.250 -0.0865 0.04150 0.03753 -0.0903 0.9855 0.0638
-3.000 -0.0214 0.03599 0.03150 -0.1017 0.9852 0.0746
-2.750 0.0317 0.03273 0.02781 -0.1089 0.9844 0.0880
-2.500 0.0985 0.02514 0.01908 -0.1166 0.9861 0.0551
-2.250 0.1450 0.02250 0.01582 -0.1205 0.9857 0.0545
-2.000 0.1869 0.02110 0.01400 -0.1234 0.9848 0.0603
-1.750 0.2228 0.02021 0.01297 -0.1252 0.9818 0.0646
-1.500 0.2581 0.01994 0.01251 -0.1267 0.9777 0.0714
-1.250 0.2968 0.01899 0.01155 -0.1290 0.9757 0.0772
-1.000 0.3357 0.01878 0.01130 -0.1313 0.9733 0.0865
-0.750 0.3724 0.01835 0.01095 -0.1333 0.9698 0.0988
-0.500 0.4078 0.01798 0.01072 -0.1351 0.9653 0.1293
-0.250 0.4483 0.01693 0.01099 -0.1385 0.9638 0.5068
0.000 0.4739 0.01608 0.01109 -0.1374 0.9605 1.0000
0.250 0.5053 0.01621 0.01109 -0.1382 0.9545 1.0000
0.500 0.5445 0.01625 0.01102 -0.1404 0.9492 1.0000
0.750 0.5837 0.01623 0.01092 -0.1426 0.9434 1.0000
1.000 0.6204 0.01616 0.01080 -0.1443 0.9367 1.0000
1.250 0.6647 0.01604 0.01067 -0.1474 0.9334 1.0000
1.500 0.6943 0.01594 0.01056 -0.1476 0.9244 1.0000
1.750 0.7410 0.01536 0.01000 -0.1506 0.9170 1.0000
2.000 0.7934 0.01431 0.00900 -0.1544 0.9074 1.0000
2.250 0.8284 0.01379 0.00854 -0.1551 0.8967 1.0000
2.500 0.8672 0.01310 0.00792 -0.1564 0.8868 1.0000
2.750 0.9069 0.01212 0.00701 -0.1574 0.8728 1.0000
3.000 0.9458 0.01114 0.00611 -0.1582 0.8472 1.0000
3.250 0.9967 0.01033 0.00532 -0.1617 0.8060 1.0000
3.500 1.0549 0.01018 0.00462 -0.1666 0.6752 1.0000
3.750 1.0650 0.01157 0.00507 -0.1624 0.5250 1.0000
4.000 1.0745 0.01292 0.00571 -0.1588 0.3798 1.0000
4.250 1.0815 0.01490 0.00667 -0.1552 0.2118 1.0000
4.500 1.0937 0.01693 0.00781 -0.1526 0.0809 1.0000
4.750 1.1153 0.01776 0.00864 -0.1513 0.0696 1.0000
5.000 1.1362 0.01864 0.00956 -0.1500 0.0640 1.0000
5.250 1.1564 0.01961 0.01060 -0.1484 0.0605 1.0000
5.500 1.1779 0.02042 0.01148 -0.1471 0.0561 1.0000
5.750 1.1980 0.02155 0.01262 -0.1457 0.0527 1.0000
6.000 1.2184 0.02331 0.01438 -0.1443 0.0495 1.0000
6.250 1.2420 0.02442 0.01563 -0.1433 0.0459 1.0000
6.500 1.2672 0.02601 0.01729 -0.1426 0.0430 1.0000
6.750 1.2984 0.02973 0.02104 -0.1434 0.0386 1.0000
7.000 1.3228 0.03108 0.02269 -0.1423 0.0368 1.0000
7.250 1.3492 0.03370 0.02564 -0.1414 0.0355 1.0000
7.500 1.3719 0.03636 0.02868 -0.1400 0.0338 1.0000
7.750 1.3916 0.03844 0.03097 -0.1387 0.0312 1.0000
8.000 1.4089 0.04231 0.03533 -0.1363 0.0311 1.0000
8.250 1.4174 0.04926 0.04315 -0.1319 0.0352 1.0000
13.500 0.9688 0.18211 0.17983 -0.1344 0.0495 1.0000
13.750 0.9582 0.18836 0.18607 -0.1397 0.0476 1.0000
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Polar data table (+)
Polar graphs
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