AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 100,000 Max Cl/Cd: 53.63 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag25-il-100000.txt Download as CSV file: xf-ag25-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG25 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4946 0.11153 0.10669 -0.0008 1.0000 0.0781
-8.750 -0.5027 0.10937 0.10463 -0.0073 1.0000 0.0796
-8.500 -0.5099 0.10669 0.10206 -0.0142 1.0000 0.0800
-8.250 -0.4815 0.10011 0.09540 -0.0052 1.0000 0.0837
-8.000 -0.4747 0.09678 0.09206 -0.0060 1.0000 0.0872
-7.750 -0.4749 0.09357 0.08892 -0.0096 1.0000 0.0913
-7.500 -0.4808 0.08929 0.08475 -0.0286 1.0000 0.0935
-7.250 -0.4680 0.08549 0.08097 -0.0159 1.0000 0.0961
-7.000 -0.4574 0.08220 0.07770 -0.0159 1.0000 0.1004
-6.750 -0.4505 0.07568 0.07114 -0.0355 1.0000 0.1075
-6.500 -0.4398 0.07296 0.06852 -0.0275 1.0000 0.1101
-6.250 -0.4270 0.06945 0.06502 -0.0293 1.0000 0.1166
-6.000 -0.4147 0.06438 0.05992 -0.0353 1.0000 0.1238
-5.750 -0.3991 0.05962 0.05502 -0.0420 1.0000 0.1357
-5.500 -0.3855 0.05717 0.05264 -0.0397 1.0000 0.1451
-5.250 -0.3700 0.05312 0.04846 -0.0437 1.0000 0.1635
-5.000 -0.3555 0.05022 0.04558 -0.0430 1.0000 0.1782
-4.750 -0.3025 0.03290 0.02645 -0.0564 1.0000 0.0701
-4.500 -0.2751 0.02869 0.02160 -0.0567 1.0000 0.0621
-4.250 -0.2475 0.02512 0.01739 -0.0567 1.0000 0.0588
-4.000 -0.2201 0.02256 0.01431 -0.0563 1.0000 0.0587
-3.750 -0.1937 0.02077 0.01222 -0.0558 1.0000 0.0626
-3.500 -0.1673 0.01909 0.01031 -0.0553 1.0000 0.0703
-3.250 -0.1404 0.01770 0.00879 -0.0547 1.0000 0.0790
-3.000 -0.1138 0.01632 0.00757 -0.0546 1.0000 0.1011
-2.750 -0.0848 0.01469 0.00634 -0.0550 1.0000 0.1679
-2.500 -0.0561 0.01302 0.00586 -0.0558 1.0000 0.4046
-2.250 -0.0320 0.01245 0.00580 -0.0550 1.0000 0.5520
-2.000 -0.0104 0.01196 0.00572 -0.0532 1.0000 0.6827
-1.750 0.0025 0.01143 0.00563 -0.0490 1.0000 0.8398
-1.500 0.0239 0.01127 0.00537 -0.0480 1.0000 1.0000
-1.250 0.0511 0.01146 0.00527 -0.0487 1.0000 1.0000
-1.000 0.0773 0.01168 0.00525 -0.0492 1.0000 1.0000
-0.750 0.1028 0.01196 0.00534 -0.0496 1.0000 1.0000
-0.500 0.1277 0.01229 0.00551 -0.0501 1.0000 1.0000
-0.250 0.1577 0.01266 0.00575 -0.0516 0.9975 1.0000
0.000 0.2120 0.01297 0.00590 -0.0574 0.9848 1.0000
0.250 0.2648 0.01320 0.00603 -0.0627 0.9710 1.0000
0.500 0.3162 0.01332 0.00611 -0.0675 0.9565 1.0000
0.750 0.3667 0.01335 0.00610 -0.0718 0.9420 1.0000
1.000 0.4105 0.01332 0.00606 -0.0746 0.9252 1.0000
1.250 0.4485 0.01325 0.00600 -0.0759 0.9062 1.0000
1.500 0.4844 0.01313 0.00590 -0.0765 0.8877 1.0000
1.750 0.5140 0.01307 0.00583 -0.0759 0.8658 1.0000
2.000 0.5426 0.01297 0.00572 -0.0748 0.8446 1.0000
2.250 0.5678 0.01297 0.00570 -0.0733 0.8195 1.0000
2.500 0.5927 0.01299 0.00572 -0.0717 0.7936 1.0000
2.750 0.6174 0.01304 0.00574 -0.0701 0.7665 1.0000
3.000 0.6421 0.01314 0.00578 -0.0686 0.7379 1.0000
3.250 0.6668 0.01328 0.00584 -0.0671 0.7081 1.0000
3.500 0.6915 0.01347 0.00600 -0.0657 0.6768 1.0000
3.750 0.7161 0.01371 0.00618 -0.0645 0.6430 1.0000
4.000 0.7408 0.01400 0.00636 -0.0633 0.6097 1.0000
4.250 0.7654 0.01434 0.00663 -0.0622 0.5736 1.0000
4.500 0.7898 0.01474 0.00691 -0.0611 0.5382 1.0000
4.750 0.8141 0.01518 0.00731 -0.0601 0.5011 1.0000
5.000 0.8382 0.01568 0.00772 -0.0592 0.4637 1.0000
5.250 0.8621 0.01624 0.00816 -0.0582 0.4271 1.0000
5.500 0.8857 0.01684 0.00868 -0.0574 0.3894 1.0000
5.750 0.9090 0.01749 0.00926 -0.0565 0.3514 1.0000
6.000 0.9319 0.01823 0.00995 -0.0556 0.3143 1.0000
6.250 0.9542 0.01905 0.01065 -0.0547 0.2776 1.0000
6.500 0.9762 0.01993 0.01148 -0.0539 0.2395 1.0000
6.750 0.9974 0.02098 0.01243 -0.0529 0.2028 1.0000
7.000 1.0176 0.02224 0.01350 -0.0520 0.1684 1.0000
7.250 1.0375 0.02357 0.01483 -0.0509 0.1339 1.0000
7.500 1.0565 0.02522 0.01638 -0.0497 0.1057 1.0000
7.750 1.0753 0.02726 0.01846 -0.0484 0.0840 1.0000
8.000 1.0940 0.02916 0.02037 -0.0472 0.0675 1.0000
8.250 1.1142 0.03189 0.02326 -0.0458 0.0579 1.0000
8.500 1.1324 0.03455 0.02600 -0.0447 0.0500 1.0000
8.750 1.1516 0.03749 0.02935 -0.0432 0.0456 1.0000
9.000 1.1683 0.04070 0.03284 -0.0419 0.0429 1.0000
9.250 1.1786 0.04614 0.03851 -0.0407 0.0405 1.0000
9.500 1.1847 0.04886 0.04192 -0.0385 0.0389 1.0000
9.750 1.1859 0.05278 0.04640 -0.0364 0.0377 1.0000
10.000 1.1815 0.05731 0.05141 -0.0345 0.0375 1.0000
10.250 1.1714 0.06195 0.05644 -0.0327 0.0377 1.0000
10.500 1.1556 0.06631 0.06110 -0.0309 0.0380 1.0000
10.750 1.1362 0.07069 0.06572 -0.0300 0.0383 1.0000
11.000 1.1153 0.07570 0.07092 -0.0309 0.0386 1.0000
11.250 1.0945 0.08148 0.07688 -0.0334 0.0389 1.0000
11.500 1.0734 0.08825 0.08378 -0.0375 0.0393 1.0000
11.750 1.0533 0.09586 0.09149 -0.0425 0.0398 1.0000
12.000 1.0360 0.10387 0.09954 -0.0471 0.0403 1.0000
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Polar data table (+)
Polar graphs
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