AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 50,000 Max Cl/Cd: 39.62 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag27-il-50000-n5.txt Download as CSV file: xf-ag27-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG27 Bubble Dancer DLG by Mark Drela
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5086 0.12272 0.11574 0.0089 1.0000 0.0868
-9.000 -0.5120 0.12099 0.11411 0.0049 1.0000 0.0886
-8.750 -0.5145 0.11893 0.11214 0.0009 1.0000 0.0892
-8.500 -0.4923 0.11209 0.10528 0.0052 1.0000 0.0939
-8.250 -0.4865 0.10883 0.10205 0.0039 1.0000 0.0974
-8.000 -0.4868 0.10639 0.09970 0.0006 1.0000 0.1013
-7.750 -0.4905 0.10446 0.09790 -0.0059 1.0000 0.1027
-7.500 -0.4798 0.09952 0.09296 -0.0052 1.0000 0.1041
-7.250 -0.4690 0.09537 0.08883 -0.0050 1.0000 0.1057
-7.000 -0.4596 0.09158 0.08509 -0.0069 1.0000 0.1070
-6.750 -0.4498 0.08771 0.08125 -0.0100 1.0000 0.1076
-6.500 -0.4318 0.07989 0.07333 -0.0180 1.0000 0.0568
-6.250 -0.4126 0.07321 0.06659 -0.0277 1.0000 0.0480
-6.000 -0.3986 0.06901 0.06238 -0.0297 1.0000 0.0463
-5.750 -0.3809 0.06419 0.05752 -0.0338 1.0000 0.0446
-5.500 -0.3602 0.05890 0.05213 -0.0387 1.0000 0.0430
-5.250 -0.3366 0.05326 0.04630 -0.0438 1.0000 0.0416
-5.000 -0.3103 0.04751 0.04023 -0.0487 1.0000 0.0404
-4.750 -0.2837 0.04270 0.03504 -0.0522 1.0000 0.0406
-4.500 -0.2569 0.03882 0.03075 -0.0545 1.0000 0.0429
-4.250 -0.2285 0.03499 0.02636 -0.0565 1.0000 0.0453
-4.000 -0.1996 0.03148 0.02223 -0.0576 1.0000 0.0466
-3.750 -0.1709 0.02849 0.01861 -0.0581 1.0000 0.0479
-3.500 -0.1435 0.02602 0.01565 -0.0580 1.0000 0.0505
-3.250 -0.1180 0.02448 0.01393 -0.0578 1.0000 0.0582
-3.000 -0.0915 0.02270 0.01183 -0.0572 1.0000 0.0643
-2.750 -0.0657 0.02142 0.01034 -0.0565 1.0000 0.0760
-2.500 -0.0395 0.02017 0.00905 -0.0561 1.0000 0.0929
-2.250 -0.0121 0.01909 0.00796 -0.0561 1.0000 0.1290
-2.000 0.0158 0.01785 0.00709 -0.0564 1.0000 0.2084
-1.750 0.0420 0.01675 0.00669 -0.0565 1.0000 0.3715
-1.500 0.0633 0.01568 0.00642 -0.0551 1.0000 0.5717
-1.250 0.0776 0.01454 0.00602 -0.0514 1.0000 1.0000
-1.000 0.1033 0.01466 0.00570 -0.0513 1.0000 1.0000
-0.750 0.1285 0.01482 0.00554 -0.0511 1.0000 1.0000
-0.500 0.1533 0.01501 0.00547 -0.0510 1.0000 1.0000
-0.250 0.1779 0.01524 0.00548 -0.0509 1.0000 1.0000
0.000 0.2021 0.01552 0.00558 -0.0509 1.0000 1.0000
0.250 0.2392 0.01582 0.00569 -0.0534 0.9898 1.0000
0.500 0.2851 0.01611 0.00583 -0.0574 0.9726 1.0000
0.750 0.3315 0.01634 0.00597 -0.0613 0.9557 1.0000
1.000 0.3748 0.01653 0.00610 -0.0644 0.9364 1.0000
1.250 0.4163 0.01667 0.00622 -0.0669 0.9163 1.0000
1.500 0.4542 0.01679 0.00634 -0.0684 0.8941 1.0000
1.750 0.4907 0.01688 0.00646 -0.0695 0.8715 1.0000
2.000 0.5225 0.01698 0.00658 -0.0695 0.8455 1.0000
2.250 0.5523 0.01709 0.00670 -0.0690 0.8182 1.0000
2.500 0.5804 0.01720 0.00681 -0.0681 0.7894 1.0000
2.750 0.6069 0.01734 0.00700 -0.0669 0.7586 1.0000
3.000 0.6321 0.01752 0.00716 -0.0654 0.7253 1.0000
3.250 0.6570 0.01772 0.00732 -0.0638 0.6913 1.0000
3.500 0.6812 0.01797 0.00754 -0.0623 0.6540 1.0000
3.750 0.7051 0.01828 0.00778 -0.0607 0.6152 1.0000
4.000 0.7286 0.01863 0.00815 -0.0592 0.5743 1.0000
4.250 0.7519 0.01906 0.00850 -0.0577 0.5311 1.0000
4.500 0.7749 0.01956 0.00891 -0.0563 0.4863 1.0000
4.750 0.7978 0.02016 0.00939 -0.0551 0.4404 1.0000
5.000 0.8208 0.02085 0.01005 -0.0540 0.3933 1.0000
5.250 0.8436 0.02166 0.01074 -0.0531 0.3481 1.0000
5.500 0.8662 0.02257 0.01155 -0.0522 0.3058 1.0000
5.750 0.8889 0.02357 0.01248 -0.0515 0.2689 1.0000
6.000 0.9114 0.02465 0.01352 -0.0508 0.2367 1.0000
6.250 0.9337 0.02581 0.01472 -0.0500 0.2089 1.0000
6.500 0.9561 0.02705 0.01600 -0.0493 0.1857 1.0000
6.750 0.9776 0.02834 0.01729 -0.0485 0.1648 1.0000
7.000 1.0000 0.02978 0.01887 -0.0476 0.1473 1.0000
7.250 1.0212 0.03121 0.02046 -0.0468 0.1294 1.0000
7.500 1.0425 0.03291 0.02233 -0.0459 0.1158 1.0000
7.750 1.0623 0.03457 0.02422 -0.0450 0.1014 1.0000
8.000 1.0823 0.03666 0.02656 -0.0440 0.0901 1.0000
8.250 1.1004 0.03876 0.02891 -0.0430 0.0790 1.0000
8.500 1.1173 0.04102 0.03130 -0.0420 0.0703 1.0000
8.750 1.1331 0.04383 0.03456 -0.0408 0.0626 1.0000
9.000 1.1452 0.04673 0.03783 -0.0397 0.0558 1.0000
9.250 1.1555 0.05028 0.04182 -0.0385 0.0514 1.0000
9.500 1.1650 0.05319 0.04474 -0.0375 0.0477 1.0000
9.750 1.1622 0.05799 0.05030 -0.0362 0.0451 1.0000
10.000 1.1554 0.06261 0.05541 -0.0352 0.0430 1.0000
10.250 1.1445 0.06716 0.06031 -0.0347 0.0418 1.0000
10.500 1.1263 0.07199 0.06540 -0.0345 0.0416 1.0000
10.750 1.1030 0.07816 0.07180 -0.0367 0.0423 1.0000
11.000 1.0780 0.08587 0.07968 -0.0414 0.0437 1.0000
11.250 1.0556 0.09448 0.08838 -0.0473 0.0451 1.0000
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Polar data table (+)
Polar graphs
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