EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 50,000 Max Cl/Cd: 24.91 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1230-il-50000-n5.txt Download as CSV file: xf-e1230-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4573 0.07762 0.07048 -0.0627 1.0000 0.0517
-10.250 -0.4859 0.07260 0.06544 -0.0638 1.0000 0.0514
-10.000 -0.5158 0.06870 0.06151 -0.0631 1.0000 0.0512
-9.750 -0.5462 0.06587 0.05865 -0.0601 1.0000 0.0510
-9.500 -0.5723 0.06298 0.05567 -0.0567 1.0000 0.0509
-9.250 -0.5941 0.06007 0.05264 -0.0532 1.0000 0.0510
-9.000 -0.6126 0.05726 0.04964 -0.0496 1.0000 0.0512
-8.750 -0.6284 0.05450 0.04661 -0.0459 1.0000 0.0516
-8.500 -0.6369 0.05227 0.04420 -0.0426 1.0000 0.0523
-8.250 -0.6369 0.05104 0.04297 -0.0398 1.0000 0.0534
-8.000 -0.6084 0.04837 0.04002 -0.0428 0.9901 0.0562
-7.750 -0.5810 0.04459 0.03554 -0.0453 0.9787 0.0594
-7.500 -0.5470 0.04259 0.03348 -0.0479 0.9670 0.0621
-7.250 -0.5163 0.04027 0.03075 -0.0495 0.9533 0.0668
-7.000 -0.4835 0.03862 0.02905 -0.0513 0.9397 0.0717
-6.750 -0.4492 0.03674 0.02691 -0.0529 0.9267 0.0784
-6.500 -0.4133 0.03523 0.02520 -0.0547 0.9142 0.0873
-6.250 -0.3749 0.03380 0.02375 -0.0568 0.9027 0.0987
-6.000 -0.3414 0.03255 0.02246 -0.0580 0.8887 0.1123
-5.750 -0.3068 0.03134 0.02123 -0.0593 0.8754 0.1288
-5.500 -0.2708 0.03010 0.02007 -0.0609 0.8632 0.1483
-5.250 -0.2359 0.02893 0.01892 -0.0622 0.8502 0.1713
-5.000 -0.2065 0.02792 0.01793 -0.0626 0.8348 0.1968
-4.750 -0.1787 0.02685 0.01700 -0.0628 0.8198 0.2278
-4.500 -0.1513 0.02572 0.01607 -0.0629 0.8055 0.2729
-4.250 -0.1259 0.02452 0.01533 -0.0626 0.7920 0.3491
-4.000 -0.1073 0.02403 0.01551 -0.0600 0.7761 0.4579
-3.750 -0.0847 0.02429 0.01594 -0.0574 0.7609 0.5514
-3.500 -0.0612 0.02459 0.01603 -0.0554 0.7466 0.6079
-3.250 -0.0362 0.02484 0.01603 -0.0536 0.7335 0.6477
-3.000 -0.0165 0.02501 0.01601 -0.0513 0.7184 0.6787
-2.750 0.0068 0.02515 0.01598 -0.0493 0.7048 0.7055
-2.500 0.0336 0.02523 0.01586 -0.0476 0.6929 0.7319
-2.250 0.0563 0.02536 0.01590 -0.0454 0.6793 0.7559
-2.000 0.0821 0.02552 0.01593 -0.0436 0.6669 0.7792
-1.750 0.1097 0.02557 0.01577 -0.0423 0.6559 0.8013
-1.500 0.1348 0.02570 0.01578 -0.0411 0.6429 0.8182
-1.250 0.1667 0.02576 0.01565 -0.0412 0.6320 0.8315
-1.000 0.1963 0.02582 0.01554 -0.0412 0.6204 0.8428
-0.750 0.2239 0.02587 0.01544 -0.0411 0.6092 0.8536
-0.500 0.2553 0.02590 0.01527 -0.0417 0.5991 0.8634
-0.250 0.2856 0.02605 0.01530 -0.0423 0.5881 0.8721
0.000 0.3173 0.02606 0.01512 -0.0430 0.5791 0.8810
0.250 0.3411 0.02622 0.01521 -0.0427 0.5685 0.8914
0.500 0.3758 0.02628 0.01507 -0.0441 0.5600 0.8993
0.750 0.4045 0.02651 0.01525 -0.0449 0.5500 0.9081
1.000 0.4376 0.02661 0.01519 -0.0461 0.5418 0.9167
1.250 0.4709 0.02689 0.01542 -0.0477 0.5324 0.9246
1.500 0.5057 0.02708 0.01549 -0.0494 0.5242 0.9332
1.750 0.5377 0.02735 0.01568 -0.0509 0.5163 0.9433
2.000 0.5725 0.02766 0.01593 -0.0529 0.5077 0.9526
2.250 0.6118 0.02782 0.01593 -0.0555 0.5012 0.9613
2.500 0.6429 0.02833 0.01651 -0.0573 0.4923 0.9733
2.750 0.6800 0.02858 0.01665 -0.0597 0.4857 0.9848
3.000 0.7145 0.02903 0.01709 -0.0620 0.4785 0.9987
3.250 0.7192 0.02945 0.01752 -0.0590 0.4724 1.0000
3.500 0.7300 0.02972 0.01770 -0.0567 0.4674 1.0000
3.750 0.7438 0.03011 0.01798 -0.0549 0.4627 1.0000
4.000 0.7495 0.03093 0.01886 -0.0520 0.4563 1.0000
4.250 0.7667 0.03147 0.01933 -0.0507 0.4510 1.0000
4.500 0.7915 0.03180 0.01951 -0.0504 0.4467 1.0000
4.750 0.8004 0.03282 0.02060 -0.0481 0.4406 1.0000
5.000 0.8144 0.03369 0.02148 -0.0466 0.4349 1.0000
5.250 0.8373 0.03421 0.02194 -0.0460 0.4305 1.0000
5.500 0.8635 0.03466 0.02228 -0.0460 0.4268 1.0000
5.750 0.8624 0.03634 0.02414 -0.0428 0.4204 1.0000
6.000 0.8769 0.03731 0.02513 -0.0414 0.4153 1.0000
6.250 0.9021 0.03779 0.02556 -0.0412 0.4114 1.0000
6.500 0.9207 0.03867 0.02643 -0.0404 0.4075 1.0000
6.750 0.9084 0.04114 0.02910 -0.0365 0.4013 1.0000
7.000 0.9180 0.04249 0.03048 -0.0349 0.3967 1.0000
7.250 0.9433 0.04299 0.03097 -0.0347 0.3933 1.0000
7.500 0.9597 0.04404 0.03202 -0.0338 0.3896 1.0000
7.750 0.8906 0.05017 0.03841 -0.0265 0.3808 1.0000
8.000 0.9001 0.05179 0.04006 -0.0256 0.3769 1.0000
8.250 0.9292 0.05201 0.04026 -0.0255 0.3744 1.0000
8.750 0.8371 0.06675 0.05523 -0.0238 0.3569 1.0000
9.000 0.8666 0.06642 0.05490 -0.0230 0.3553 1.0000
10.500 0.7555 0.10187 0.09069 -0.0296 0.3148 1.0000
10.750 0.7549 0.10545 0.09432 -0.0302 0.3098 1.0000
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Polar data table (+)
Polar graphs
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