EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 200,000 Max Cl/Cd: 62.2 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e850-il-200000-n5.txt Download as CSV file: xf-e850-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.5727 0.06107 0.05759 -0.0381 1.0000 0.0100
-6.750 -0.5703 0.05573 0.05207 -0.0408 0.9983 0.0095
-6.500 -0.5559 0.04965 0.04570 -0.0452 0.9949 0.0088
-6.250 -0.5377 0.04433 0.04004 -0.0481 0.9922 0.0081
-6.000 -0.5177 0.03951 0.03483 -0.0498 0.9891 0.0075
-5.750 -0.4945 0.03485 0.02971 -0.0511 0.9865 0.0069
-5.500 -0.4688 0.03045 0.02479 -0.0519 0.9845 0.0062
-5.250 -0.4406 0.02664 0.02040 -0.0524 0.9829 0.0057
-5.000 -0.4113 0.02362 0.01688 -0.0527 0.9818 0.0053
-4.750 -0.3825 0.02133 0.01407 -0.0527 0.9807 0.0050
-4.500 -0.3574 0.01965 0.01213 -0.0521 0.9787 0.0048
-4.250 -0.3310 0.01827 0.01056 -0.0518 0.9768 0.0047
-4.000 -0.3036 0.01704 0.00916 -0.0518 0.9749 0.0047
-3.750 -0.2752 0.01594 0.00790 -0.0522 0.9732 0.0047
-3.500 -0.2453 0.01511 0.00686 -0.0528 0.9717 0.0050
-3.250 -0.2142 0.01454 0.00605 -0.0536 0.9702 0.0055
-3.000 -0.1823 0.01416 0.00546 -0.0545 0.9689 0.0069
-2.750 -0.1556 0.01341 0.00500 -0.0548 0.9666 0.0787
-2.500 -0.1312 0.01178 0.00466 -0.0557 0.9646 0.4142
-2.250 -0.1061 0.01148 0.00498 -0.0552 0.9620 0.5814
-2.000 -0.0768 0.01148 0.00499 -0.0556 0.9597 0.6136
-1.750 -0.0457 0.01147 0.00494 -0.0564 0.9578 0.6275
-1.500 -0.0133 0.01146 0.00490 -0.0575 0.9562 0.6383
-1.250 0.0125 0.01144 0.00488 -0.0572 0.9527 0.6478
-1.000 0.0404 0.01143 0.00483 -0.0573 0.9494 0.6580
-0.750 0.0710 0.01141 0.00481 -0.0581 0.9468 0.6684
-0.500 0.1033 0.01139 0.00481 -0.0592 0.9446 0.6799
-0.250 0.1372 0.01137 0.00482 -0.0606 0.9429 0.6918
0.000 0.1604 0.01135 0.00486 -0.0597 0.9374 0.7039
0.250 0.1916 0.01130 0.00489 -0.0605 0.9340 0.7169
0.500 0.2258 0.01122 0.00489 -0.0619 0.9314 0.7311
0.750 0.2545 0.01115 0.00494 -0.0621 0.9269 0.7462
1.000 0.2841 0.01106 0.00496 -0.0625 0.9218 0.7630
1.250 0.3204 0.01088 0.00492 -0.0641 0.9185 0.7816
1.500 0.3486 0.01072 0.00492 -0.0640 0.9114 0.8026
1.750 0.3866 0.01038 0.00477 -0.0657 0.9059 0.8257
2.000 0.4205 0.01000 0.00472 -0.0663 0.8948 0.8533
2.250 0.4578 0.00941 0.00433 -0.0671 0.8734 0.8864
2.500 0.4982 0.00891 0.00400 -0.0688 0.8391 0.9305
2.750 0.5536 0.00890 0.00331 -0.0729 0.6294 0.9634
3.000 0.5571 0.01064 0.00373 -0.0682 0.3655 1.0000
3.250 0.5691 0.01206 0.00427 -0.0658 0.1764 1.0000
3.500 0.5877 0.01312 0.00495 -0.0644 0.0738 1.0000
3.750 0.6083 0.01412 0.00571 -0.0632 0.0283 1.0000
4.000 0.6299 0.01508 0.00671 -0.0619 0.0134 1.0000
4.250 0.6515 0.01614 0.00793 -0.0604 0.0108 1.0000
4.500 0.6731 0.01745 0.00937 -0.0590 0.0096 1.0000
4.750 0.6967 0.01903 0.01108 -0.0578 0.0089 1.0000
5.000 0.7225 0.02094 0.01318 -0.0570 0.0084 1.0000
5.250 0.7460 0.02312 0.01557 -0.0563 0.0063 1.0000
5.500 0.7707 0.02438 0.01709 -0.0556 0.0043 1.0000
5.750 0.7943 0.02691 0.02002 -0.0543 0.0038 1.0000
6.000 0.8149 0.03009 0.02368 -0.0523 0.0035 1.0000
6.250 0.8318 0.03374 0.02782 -0.0498 0.0034 1.0000
6.500 0.8452 0.03787 0.03241 -0.0470 0.0034 1.0000
6.750 0.8556 0.04222 0.03720 -0.0440 0.0034 1.0000
7.000 0.8631 0.04670 0.04204 -0.0410 0.0034 1.0000
7.250 0.8679 0.05125 0.04692 -0.0383 0.0035 1.0000
7.500 0.8697 0.05586 0.05181 -0.0356 0.0036 1.0000
7.750 0.8686 0.06042 0.05661 -0.0333 0.0037 1.0000
8.000 0.8641 0.06496 0.06135 -0.0312 0.0037 1.0000
8.250 0.8567 0.06924 0.06579 -0.0294 0.0038 1.0000
8.500 0.8436 0.07318 0.06984 -0.0273 0.0038 1.0000
8.750 0.8287 0.07733 0.07408 -0.0263 0.0039 1.0000
9.000 0.8138 0.08207 0.07889 -0.0272 0.0039 1.0000
9.250 0.8006 0.08777 0.08464 -0.0304 0.0040 1.0000
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Polar data table (+)
Polar graphs
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