AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.38 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag27-il-1000000-n5.txt Download as CSV file: xf-ag27-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5245 0.10660 0.10499 0.0135 1.0000 0.0029
-8.750 -0.5207 0.10250 0.10091 0.0116 1.0000 0.0028
-8.500 -0.5169 0.09844 0.09686 0.0096 1.0000 0.0028
-8.250 -0.5128 0.09447 0.09291 0.0075 1.0000 0.0029
-8.000 -0.5088 0.09050 0.08895 0.0053 1.0000 0.0029
-7.750 -0.5047 0.08652 0.08499 0.0028 1.0000 0.0030
-7.500 -0.4994 0.08223 0.08072 -0.0007 1.0000 0.0032
-7.250 -0.4887 0.07702 0.07552 -0.0065 1.0000 0.0034
-7.000 -0.4746 0.07101 0.06951 -0.0139 1.0000 0.0036
-6.750 -0.4565 0.06448 0.06296 -0.0223 1.0000 0.0037
-6.500 -0.4338 0.05697 0.05540 -0.0321 1.0000 0.0038
-6.250 -0.4062 0.04753 0.04584 -0.0433 1.0000 0.0038
-6.000 -0.3749 0.01973 0.01671 -0.0605 1.0000 0.0039
-5.750 -0.3437 0.01578 0.01216 -0.0626 0.9968 0.0040
-5.500 -0.3113 0.01338 0.00932 -0.0641 0.9923 0.0040
-5.250 -0.2792 0.01185 0.00749 -0.0653 0.9862 0.0041
-5.000 -0.2471 0.01077 0.00621 -0.0663 0.9792 0.0041
-4.750 -0.2153 0.00999 0.00525 -0.0671 0.9697 0.0042
-4.500 -0.1854 0.00898 0.00404 -0.0675 0.9565 0.0045
-4.250 -0.1573 0.00849 0.00345 -0.0674 0.9405 0.0050
-4.000 -0.1306 0.00821 0.00309 -0.0670 0.9217 0.0055
-3.750 -0.1042 0.00797 0.00274 -0.0664 0.9019 0.0061
-3.500 -0.0774 0.00777 0.00241 -0.0660 0.8820 0.0066
-3.250 -0.0504 0.00760 0.00213 -0.0656 0.8619 0.0070
-3.000 -0.0231 0.00737 0.00179 -0.0653 0.8418 0.0084
-2.750 0.0043 0.00726 0.00159 -0.0650 0.8204 0.0103
-2.500 0.0319 0.00712 0.00138 -0.0648 0.7990 0.0139
-2.250 0.0595 0.00704 0.00121 -0.0646 0.7768 0.0194
-2.000 0.0872 0.00696 0.00107 -0.0644 0.7544 0.0290
-1.750 0.1149 0.00687 0.00096 -0.0643 0.7314 0.0464
-1.500 0.1427 0.00677 0.00086 -0.0642 0.7078 0.0717
-1.250 0.1706 0.00669 0.00078 -0.0642 0.6842 0.1051
-1.000 0.1984 0.00661 0.00072 -0.0641 0.6602 0.1437
-0.750 0.2262 0.00655 0.00068 -0.0641 0.6356 0.1849
-0.500 0.2540 0.00649 0.00065 -0.0641 0.6091 0.2336
-0.250 0.2818 0.00645 0.00064 -0.0641 0.5822 0.2826
0.000 0.3095 0.00643 0.00065 -0.0641 0.5541 0.3353
0.250 0.3372 0.00643 0.00067 -0.0640 0.5257 0.3829
0.500 0.3649 0.00643 0.00070 -0.0640 0.4973 0.4370
0.750 0.3925 0.00644 0.00075 -0.0640 0.4683 0.4962
1.000 0.4201 0.00641 0.00081 -0.0640 0.4393 0.5715
1.250 0.4471 0.00625 0.00089 -0.0639 0.4116 0.6979
1.750 0.4981 0.00590 0.00101 -0.0626 0.3582 1.0000
2.000 0.5256 0.00612 0.00109 -0.0625 0.3294 1.0000
2.250 0.5531 0.00633 0.00118 -0.0625 0.3020 1.0000
2.750 0.6081 0.00677 0.00140 -0.0623 0.2507 1.0000
3.000 0.6353 0.00702 0.00153 -0.0622 0.2232 1.0000
3.250 0.6627 0.00725 0.00166 -0.0621 0.2024 1.0000
3.500 0.6899 0.00749 0.00181 -0.0620 0.1803 1.0000
3.750 0.7171 0.00774 0.00199 -0.0619 0.1601 1.0000
4.000 0.7444 0.00796 0.00215 -0.0618 0.1456 1.0000
4.250 0.7715 0.00821 0.00233 -0.0617 0.1303 1.0000
4.500 0.7986 0.00846 0.00252 -0.0615 0.1153 1.0000
4.750 0.8257 0.00869 0.00273 -0.0614 0.1047 1.0000
5.000 0.8526 0.00896 0.00295 -0.0613 0.0922 1.0000
5.250 0.8794 0.00922 0.00318 -0.0611 0.0822 1.0000
5.500 0.9061 0.00952 0.00343 -0.0609 0.0712 1.0000
5.750 0.9328 0.00979 0.00368 -0.0608 0.0633 1.0000
6.000 0.9594 0.01008 0.00396 -0.0606 0.0554 1.0000
6.250 0.9857 0.01042 0.00427 -0.0604 0.0461 1.0000
6.500 1.0118 0.01079 0.00460 -0.0601 0.0378 1.0000
6.750 1.0379 0.01114 0.00494 -0.0599 0.0310 1.0000
7.000 1.0638 0.01153 0.00532 -0.0597 0.0243 1.0000
7.250 1.0893 0.01198 0.00575 -0.0594 0.0180 1.0000
7.500 1.1149 0.01239 0.00618 -0.0591 0.0145 1.0000
7.750 1.1402 0.01285 0.00664 -0.0587 0.0110 1.0000
8.000 1.1651 0.01337 0.00716 -0.0584 0.0080 1.0000
8.250 1.1900 0.01385 0.00768 -0.0580 0.0062 1.0000
8.500 1.2145 0.01441 0.00827 -0.0576 0.0048 1.0000
8.750 1.2391 0.01494 0.00888 -0.0572 0.0041 1.0000
9.000 1.2634 0.01547 0.00948 -0.0568 0.0036 1.0000
9.250 1.2873 0.01608 0.01014 -0.0563 0.0031 1.0000
9.500 1.3104 0.01681 0.01096 -0.0557 0.0027 1.0000
9.750 1.3331 0.01757 0.01182 -0.0551 0.0024 1.0000
10.000 1.3560 0.01824 0.01258 -0.0545 0.0023 1.0000
10.250 1.3783 0.01898 0.01341 -0.0539 0.0021 1.0000
10.500 1.4000 0.01977 0.01431 -0.0532 0.0020 1.0000
10.750 1.4211 0.02062 0.01529 -0.0525 0.0018 1.0000
11.000 1.4415 0.02153 0.01630 -0.0517 0.0017 1.0000
11.250 1.4609 0.02251 0.01740 -0.0508 0.0016 1.0000
11.500 1.4790 0.02363 0.01865 -0.0498 0.0015 1.0000
11.750 1.4951 0.02497 0.02014 -0.0486 0.0014 1.0000
12.000 1.5078 0.02663 0.02198 -0.0471 0.0013 1.0000
12.250 1.5137 0.02898 0.02458 -0.0451 0.0012 1.0000
12.500 1.5250 0.03044 0.02619 -0.0436 0.0012 1.0000
12.750 1.5343 0.03196 0.02785 -0.0419 0.0012 1.0000
13.000 1.5388 0.03355 0.02958 -0.0397 0.0011 1.0000
13.250 1.5369 0.03548 0.03166 -0.0372 0.0011 1.0000
13.500 1.5338 0.03775 0.03410 -0.0354 0.0011 1.0000
13.750 1.5272 0.04077 0.03729 -0.0346 0.0011 1.0000
14.000 1.5197 0.04442 0.04110 -0.0350 0.0011 1.0000
14.250 1.5084 0.04923 0.04609 -0.0367 0.0011 1.0000
14.500 1.4949 0.05512 0.05216 -0.0399 0.0011 1.0000
14.750 1.4739 0.06313 0.06036 -0.0449 0.0011 1.0000
15.000 1.4463 0.07308 0.07050 -0.0511 0.0011 1.0000
15.250 1.4060 0.08602 0.08363 -0.0585 0.0011 1.0000
15.500 1.3589 0.10033 0.09809 -0.0659 0.0011 1.0000
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Polar data table (+)
Polar graphs
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