EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 100,000 Max Cl/Cd: 41.53 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e850-il-100000-n5.txt Download as CSV file: xf-e850-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E850 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5036 0.09771 0.09261 -0.0310 1.0000 0.0137
-9.000 -0.5075 0.09323 0.08821 -0.0325 1.0000 0.0131
-8.500 -0.5177 0.08353 0.07866 -0.0364 1.0000 0.0119
-8.000 -0.4530 0.06609 0.06148 -0.0395 1.0000 0.0108
-7.750 -0.4675 0.06162 0.05705 -0.0404 1.0000 0.0107
-7.500 -0.4872 0.05820 0.05364 -0.0403 1.0000 0.0106
-7.250 -0.5524 0.06495 0.06002 -0.0410 1.0000 0.0108
-7.000 -0.5595 0.06104 0.05603 -0.0409 1.0000 0.0106
-6.750 -0.5629 0.05711 0.05196 -0.0406 1.0000 0.0104
-6.500 -0.5629 0.05300 0.04765 -0.0404 1.0000 0.0102
-6.250 -0.5584 0.04899 0.04339 -0.0402 1.0000 0.0100
-6.000 -0.5499 0.04509 0.03918 -0.0400 1.0000 0.0098
-5.750 -0.5378 0.04122 0.03494 -0.0397 1.0000 0.0096
-5.500 -0.5221 0.03753 0.03082 -0.0394 1.0000 0.0094
-5.250 -0.5035 0.03420 0.02703 -0.0390 1.0000 0.0092
-5.000 -0.4823 0.03114 0.02348 -0.0385 1.0000 0.0091
-4.750 -0.4594 0.02841 0.02028 -0.0380 1.0000 0.0089
-4.500 -0.4351 0.02597 0.01726 -0.0373 1.0000 0.0089
-4.250 -0.4105 0.02398 0.01494 -0.0366 1.0000 0.0089
-4.000 -0.3860 0.02223 0.01294 -0.0358 1.0000 0.0090
-3.750 -0.3617 0.02073 0.01124 -0.0350 1.0000 0.0093
-3.500 -0.3374 0.01951 0.00981 -0.0344 1.0000 0.0098
-3.250 -0.3124 0.01857 0.00859 -0.0340 1.0000 0.0106
-3.000 -0.2872 0.01769 0.00756 -0.0338 1.0000 0.0178
-2.750 -0.2605 0.01460 0.00669 -0.0355 1.0000 0.4351
-2.500 -0.2421 0.01446 0.00703 -0.0330 1.0000 0.6047
-2.250 -0.2214 0.01449 0.00701 -0.0312 1.0000 0.6494
-2.000 -0.2005 0.01451 0.00696 -0.0296 1.0000 0.6800
-1.750 -0.1779 0.01449 0.00670 -0.0287 1.0000 0.6957
-1.500 -0.1508 0.01452 0.00661 -0.0288 0.9984 0.7093
-1.250 -0.1201 0.01462 0.00661 -0.0296 0.9953 0.7232
-1.000 -0.0891 0.01472 0.00664 -0.0305 0.9923 0.7376
-0.750 -0.0593 0.01478 0.00666 -0.0312 0.9888 0.7526
-0.500 -0.0285 0.01489 0.00668 -0.0321 0.9852 0.7691
-0.250 0.0033 0.01502 0.00682 -0.0332 0.9819 0.7871
0.000 0.0321 0.01506 0.00689 -0.0336 0.9777 0.8079
0.250 0.0613 0.01509 0.00699 -0.0341 0.9732 0.8329
0.500 0.0937 0.01516 0.00716 -0.0352 0.9694 0.8664
0.750 0.1284 0.01510 0.00723 -0.0368 0.9648 0.9239
1.000 0.1666 0.01513 0.00729 -0.0396 0.9594 1.0000
1.250 0.2046 0.01536 0.00751 -0.0422 0.9554 1.0000
1.500 0.2347 0.01546 0.00765 -0.0432 0.9482 1.0000
1.750 0.2735 0.01564 0.00789 -0.0458 0.9434 1.0000
2.000 0.3045 0.01573 0.00806 -0.0467 0.9351 1.0000
2.250 0.3432 0.01581 0.00828 -0.0491 0.9282 1.0000
2.500 0.3809 0.01580 0.00863 -0.0511 0.9187 1.0000
2.750 0.4204 0.01562 0.00868 -0.0531 0.9061 1.0000
3.000 0.4657 0.01495 0.00830 -0.0554 0.8834 1.0000
3.250 0.5110 0.01375 0.00740 -0.0565 0.8402 1.0000
3.500 0.5819 0.01401 0.00601 -0.0611 0.3723 1.0000
3.750 0.5937 0.01643 0.00692 -0.0589 0.1009 1.0000
4.000 0.6129 0.01794 0.00811 -0.0573 0.0458 1.0000
4.250 0.6331 0.01929 0.00953 -0.0556 0.0304 1.0000
4.500 0.6534 0.02076 0.01111 -0.0540 0.0220 1.0000
4.750 0.6756 0.02222 0.01263 -0.0530 0.0168 1.0000
5.000 0.7007 0.02522 0.01575 -0.0521 0.0151 1.0000
5.250 0.7284 0.02750 0.01833 -0.0515 0.0145 1.0000
5.500 0.7546 0.03018 0.02141 -0.0505 0.0140 1.0000
5.750 0.7777 0.03321 0.02494 -0.0489 0.0137 1.0000
6.000 0.7970 0.03655 0.02879 -0.0469 0.0135 1.0000
6.250 0.8128 0.04010 0.03284 -0.0446 0.0134 1.0000
6.500 0.8251 0.04394 0.03715 -0.0420 0.0134 1.0000
6.750 0.8359 0.04768 0.04133 -0.0394 0.0130 1.0000
7.000 0.8444 0.05153 0.04558 -0.0369 0.0122 1.0000
7.250 0.8502 0.05550 0.04990 -0.0345 0.0113 1.0000
7.500 0.8528 0.05955 0.05425 -0.0323 0.0105 1.0000
7.750 0.8523 0.06363 0.05858 -0.0303 0.0099 1.0000
8.000 0.8490 0.06753 0.06267 -0.0286 0.0091 1.0000
8.250 0.8408 0.07191 0.06723 -0.0270 0.0096 1.0000
8.500 0.8283 0.07581 0.07124 -0.0253 0.0095 1.0000
8.750 0.8143 0.08012 0.07564 -0.0249 0.0097 1.0000
9.000 0.8001 0.08518 0.08076 -0.0262 0.0103 1.0000
9.250 0.7885 0.09090 0.08651 -0.0295 0.0106 1.0000
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Polar data table (+)
Polar graphs
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