AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 100,000 Max Cl/Cd: 55.13 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag27-il-100000.txt Download as CSV file: xf-ag27-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4815 0.10209 0.09732 0.0036 1.0000 0.0691
-7.750 -0.4769 0.09892 0.09417 0.0015 1.0000 0.0718
-7.500 -0.4763 0.09641 0.09173 -0.0037 1.0000 0.0744
-7.250 -0.4658 0.09331 0.08870 -0.0195 1.0000 0.0756
-7.000 -0.4602 0.08793 0.08335 -0.0114 1.0000 0.0773
-6.750 -0.4492 0.08446 0.07989 -0.0094 1.0000 0.0803
-6.500 -0.4370 0.08082 0.07628 -0.0128 1.0000 0.0846
-6.250 -0.4131 0.07524 0.07063 -0.0310 1.0000 0.0898
-6.000 -0.4069 0.07193 0.06742 -0.0243 1.0000 0.0922
-5.750 -0.3917 0.06851 0.06400 -0.0256 1.0000 0.0974
-5.500 -0.3673 0.06307 0.05846 -0.0355 1.0000 0.1048
-5.250 -0.3527 0.06025 0.05568 -0.0344 1.0000 0.1125
-5.000 -0.3334 0.05635 0.05175 -0.0374 1.0000 0.1227
-4.750 -0.3121 0.05259 0.04792 -0.0405 1.0000 0.1357
-4.500 -0.2900 0.04898 0.04421 -0.0431 1.0000 0.1493
-4.250 -0.2614 0.04551 0.04046 -0.0481 1.0000 0.1731
-4.000 -0.2445 0.04255 0.03761 -0.0465 1.0000 0.1816
-3.750 -0.1934 0.03405 0.02816 -0.0560 1.0000 0.1328
-3.500 -0.1430 0.02459 0.01691 -0.0586 1.0000 0.0605
-3.250 -0.1148 0.02205 0.01387 -0.0585 1.0000 0.0606
-3.000 -0.0879 0.01998 0.01152 -0.0583 1.0000 0.0663
-2.750 -0.0605 0.01831 0.00962 -0.0578 1.0000 0.0710
-2.500 -0.0333 0.01681 0.00801 -0.0574 1.0000 0.0814
-2.250 -0.0061 0.01557 0.00672 -0.0569 1.0000 0.1011
-2.000 0.0216 0.01425 0.00570 -0.0569 1.0000 0.1493
-1.750 0.0504 0.01257 0.00507 -0.0575 1.0000 0.3548
-1.500 0.0745 0.01126 0.00490 -0.0565 1.0000 0.6507
-1.250 0.0921 0.01054 0.00460 -0.0536 1.0000 1.0000
-1.000 0.1184 0.01069 0.00441 -0.0536 1.0000 1.0000
-0.750 0.1441 0.01087 0.00436 -0.0537 1.0000 1.0000
-0.500 0.1693 0.01109 0.00439 -0.0537 1.0000 1.0000
-0.250 0.1941 0.01136 0.00451 -0.0538 1.0000 1.0000
0.000 0.2185 0.01169 0.00470 -0.0540 1.0000 1.0000
0.250 0.2424 0.01207 0.00499 -0.0543 1.0000 1.0000
0.500 0.2911 0.01239 0.00521 -0.0591 0.9878 1.0000
0.750 0.3464 0.01259 0.00535 -0.0649 0.9718 1.0000
1.000 0.4017 0.01265 0.00539 -0.0703 0.9557 1.0000
1.250 0.4482 0.01264 0.00539 -0.0736 0.9356 1.0000
1.500 0.4913 0.01255 0.00534 -0.0758 0.9153 1.0000
1.750 0.5252 0.01248 0.00528 -0.0760 0.8909 1.0000
2.000 0.5543 0.01243 0.00522 -0.0750 0.8650 1.0000
2.250 0.5800 0.01241 0.00519 -0.0733 0.8371 1.0000
2.500 0.6041 0.01244 0.00518 -0.0714 0.8076 1.0000
2.750 0.6278 0.01251 0.00523 -0.0694 0.7767 1.0000
3.000 0.6513 0.01262 0.00527 -0.0674 0.7439 1.0000
3.250 0.6750 0.01279 0.00536 -0.0657 0.7082 1.0000
3.500 0.6988 0.01300 0.00548 -0.0641 0.6706 1.0000
3.750 0.7226 0.01326 0.00568 -0.0625 0.6305 1.0000
4.000 0.7464 0.01358 0.00587 -0.0611 0.5868 1.0000
4.250 0.7701 0.01397 0.00611 -0.0597 0.5401 1.0000
4.500 0.7935 0.01444 0.00641 -0.0585 0.4884 1.0000
4.750 0.8166 0.01503 0.00679 -0.0573 0.4339 1.0000
5.000 0.8394 0.01577 0.00733 -0.0563 0.3781 1.0000
5.250 0.8620 0.01666 0.00794 -0.0553 0.3257 1.0000
5.500 0.8849 0.01763 0.00870 -0.0545 0.2803 1.0000
5.750 0.9078 0.01869 0.00955 -0.0537 0.2438 1.0000
6.000 0.9311 0.01978 0.01059 -0.0529 0.2133 1.0000
6.250 0.9544 0.02096 0.01167 -0.0522 0.1886 1.0000
6.500 0.9778 0.02213 0.01279 -0.0515 0.1664 1.0000
6.750 1.0013 0.02353 0.01420 -0.0508 0.1480 1.0000
7.000 1.0243 0.02480 0.01558 -0.0500 0.1297 1.0000
7.250 1.0474 0.02637 0.01721 -0.0492 0.1146 1.0000
7.500 1.0694 0.02791 0.01884 -0.0484 0.0997 1.0000
7.750 1.0913 0.02981 0.02090 -0.0475 0.0868 1.0000
8.000 1.1121 0.03188 0.02322 -0.0464 0.0751 1.0000
8.250 1.1313 0.03431 0.02596 -0.0453 0.0651 1.0000
8.500 1.1490 0.03754 0.02938 -0.0442 0.0584 1.0000
8.750 1.1642 0.04062 0.03309 -0.0425 0.0528 1.0000
9.000 1.1773 0.04419 0.03668 -0.0417 0.0476 1.0000
9.250 1.1831 0.04852 0.04181 -0.0396 0.0461 1.0000
9.500 1.1828 0.05371 0.04763 -0.0378 0.0454 1.0000
9.750 1.1765 0.05912 0.05357 -0.0363 0.0453 1.0000
10.000 1.1647 0.06447 0.05931 -0.0352 0.0454 1.0000
10.250 1.1482 0.06956 0.06470 -0.0344 0.0457 1.0000
10.500 1.1280 0.07434 0.06967 -0.0341 0.0461 1.0000
10.750 1.1078 0.07975 0.07523 -0.0357 0.0466 1.0000
11.000 1.0884 0.08606 0.08163 -0.0389 0.0471 1.0000
11.250 1.0715 0.09312 0.08876 -0.0428 0.0476 1.0000
11.500 0.9859 0.12644 0.12209 -0.0701 0.0695 1.0000
11.750 0.9831 0.13247 0.12811 -0.0716 0.0708 1.0000
12.000 0.9835 0.13812 0.13375 -0.0722 0.0715 1.0000
12.250 0.7768 0.14692 0.14257 -0.0639 0.1362 1.0000
12.500 0.7524 0.14921 0.14482 -0.0666 0.1331 1.0000
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Polar data table (+)
Polar graphs
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