AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 100,000 Max Cl/Cd: 52.62 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag24-il-100000.txt Download as CSV file: xf-ag24-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG24 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3902 0.11930 0.11459 -0.0079 1.0000 0.0825
-10.250 -0.3958 0.11639 0.11171 -0.0100 1.0000 0.0856
-10.000 -0.5102 0.12212 0.11717 0.0022 1.0000 0.0773
-9.750 -0.5028 0.11862 0.11368 0.0016 1.0000 0.0803
-9.500 -0.3872 0.10472 0.10012 -0.0119 1.0000 0.0915
-9.250 -0.3835 0.10120 0.09662 -0.0125 1.0000 0.0951
-9.000 -0.3902 0.09779 0.09326 -0.0150 1.0000 0.0990
-8.750 -0.4106 0.09478 0.09035 -0.0204 1.0000 0.1005
-8.500 -0.3857 0.08955 0.08510 -0.0162 1.0000 0.1044
-8.250 -0.3830 0.08614 0.08172 -0.0168 1.0000 0.1108
-8.000 -0.3998 0.08256 0.07824 -0.0215 1.0000 0.1136
-7.750 -0.4830 0.08906 0.08452 -0.0142 1.0000 0.1039
-7.500 -0.4756 0.08589 0.08138 -0.0146 1.0000 0.1089
-7.250 -0.4847 0.07905 0.07457 -0.0346 1.0000 0.1148
-7.000 -0.4666 0.07768 0.07328 -0.0219 1.0000 0.1197
-6.750 -0.4661 0.07072 0.06622 -0.0386 1.0000 0.1287
-6.500 -0.4501 0.06956 0.06520 -0.0291 1.0000 0.1363
-6.250 -0.4420 0.06484 0.06047 -0.0338 1.0000 0.1457
-6.000 -0.4324 0.06039 0.05592 -0.0383 1.0000 0.1579
-5.750 -0.4210 0.05658 0.05202 -0.0409 1.0000 0.1711
-5.500 -0.3892 0.03794 0.03187 -0.0536 1.0000 0.0713
-5.250 -0.3646 0.03236 0.02530 -0.0541 1.0000 0.0599
-5.000 -0.3420 0.02861 0.02116 -0.0540 1.0000 0.0582
-4.750 -0.3173 0.02566 0.01768 -0.0536 1.0000 0.0578
-4.500 -0.2917 0.02366 0.01515 -0.0529 1.0000 0.0601
-4.250 -0.2674 0.02148 0.01288 -0.0526 1.0000 0.0661
-4.000 -0.2414 0.01985 0.01104 -0.0518 1.0000 0.0713
-3.750 -0.2158 0.01831 0.00951 -0.0514 1.0000 0.0818
-3.500 -0.1895 0.01704 0.00821 -0.0509 1.0000 0.1009
-3.250 -0.1618 0.01541 0.00699 -0.0513 1.0000 0.1577
-3.000 -0.1332 0.01376 0.00637 -0.0522 1.0000 0.3510
-2.750 -0.1087 0.01324 0.00630 -0.0518 1.0000 0.4741
-2.500 -0.0852 0.01290 0.00627 -0.0509 1.0000 0.5711
-2.250 -0.0631 0.01262 0.00626 -0.0494 1.0000 0.6613
-2.000 -0.0439 0.01240 0.00626 -0.0470 1.0000 0.7495
-1.750 -0.0311 0.01216 0.00623 -0.0432 1.0000 0.8462
-1.500 -0.0150 0.01192 0.00601 -0.0411 1.0000 1.0000
-1.250 0.0139 0.01213 0.00594 -0.0426 1.0000 1.0000
-1.000 0.0407 0.01240 0.00600 -0.0436 1.0000 1.0000
-0.750 0.0664 0.01273 0.00613 -0.0444 1.0000 1.0000
-0.500 0.1154 0.01308 0.00629 -0.0494 0.9902 1.0000
-0.250 0.1679 0.01337 0.00643 -0.0548 0.9781 1.0000
0.000 0.2190 0.01359 0.00652 -0.0598 0.9652 1.0000
0.250 0.2685 0.01372 0.00658 -0.0642 0.9515 1.0000
0.500 0.3174 0.01377 0.00659 -0.0684 0.9377 1.0000
0.750 0.3612 0.01375 0.00655 -0.0712 0.9224 1.0000
1.000 0.4009 0.01369 0.00647 -0.0730 0.9061 1.0000
1.250 0.4372 0.01360 0.00638 -0.0739 0.8891 1.0000
1.500 0.4705 0.01347 0.00624 -0.0739 0.8719 1.0000
1.750 0.4978 0.01344 0.00620 -0.0730 0.8505 1.0000
2.000 0.5256 0.01335 0.00609 -0.0719 0.8307 1.0000
2.250 0.5509 0.01336 0.00611 -0.0705 0.8075 1.0000
2.500 0.5765 0.01336 0.00607 -0.0691 0.7848 1.0000
2.750 0.6018 0.01339 0.00605 -0.0676 0.7607 1.0000
3.000 0.6268 0.01349 0.00611 -0.0663 0.7345 1.0000
3.250 0.6519 0.01362 0.00623 -0.0651 0.7075 1.0000
3.500 0.6771 0.01379 0.00634 -0.0639 0.6797 1.0000
3.750 0.7023 0.01400 0.00648 -0.0627 0.6511 1.0000
4.000 0.7274 0.01425 0.00666 -0.0617 0.6217 1.0000
4.250 0.7525 0.01456 0.00689 -0.0606 0.5915 1.0000
4.500 0.7773 0.01490 0.00723 -0.0597 0.5596 1.0000
4.750 0.8021 0.01528 0.00755 -0.0588 0.5275 1.0000
5.000 0.8266 0.01571 0.00788 -0.0578 0.4956 1.0000
5.250 0.8508 0.01617 0.00831 -0.0570 0.4617 1.0000
5.500 0.8748 0.01668 0.00879 -0.0561 0.4277 1.0000
5.750 0.8983 0.01724 0.00929 -0.0552 0.3925 1.0000
6.000 0.9214 0.01785 0.00982 -0.0543 0.3571 1.0000
6.250 0.9440 0.01852 0.01045 -0.0534 0.3200 1.0000
6.500 0.9659 0.01927 0.01111 -0.0524 0.2826 1.0000
6.750 0.9868 0.02015 0.01185 -0.0515 0.2445 1.0000
7.000 1.0069 0.02116 0.01281 -0.0504 0.2042 1.0000
7.250 1.0256 0.02245 0.01394 -0.0493 0.1634 1.0000
7.500 1.0432 0.02400 0.01535 -0.0481 0.1246 1.0000
7.750 1.0598 0.02594 0.01712 -0.0467 0.0950 1.0000
8.000 1.0777 0.02797 0.01917 -0.0452 0.0752 1.0000
8.250 1.0959 0.03010 0.02130 -0.0438 0.0622 1.0000
8.500 1.1160 0.03290 0.02423 -0.0425 0.0546 1.0000
8.750 1.1342 0.03572 0.02700 -0.0417 0.0475 1.0000
9.000 1.1527 0.03871 0.03053 -0.0400 0.0448 1.0000
9.250 1.1680 0.04222 0.03454 -0.0383 0.0429 1.0000
9.500 1.1787 0.04591 0.03871 -0.0365 0.0416 1.0000
9.750 1.1880 0.04906 0.04217 -0.0350 0.0396 1.0000
10.000 1.1952 0.05232 0.04557 -0.0338 0.0374 1.0000
10.250 1.1932 0.05738 0.05096 -0.0322 0.0365 1.0000
10.500 1.1862 0.06196 0.05591 -0.0303 0.0364 1.0000
10.750 1.1765 0.06569 0.06000 -0.0284 0.0366 1.0000
11.000 1.1602 0.06908 0.06370 -0.0263 0.0369 1.0000
11.250 1.1382 0.07308 0.06801 -0.0256 0.0374 1.0000
11.500 1.1062 0.07903 0.07431 -0.0279 0.0383 1.0000
11.750 1.0437 0.09293 0.08863 -0.0385 0.0430 1.0000
12.000 1.0192 0.10251 0.09829 -0.0450 0.0448 1.0000
12.250 1.0015 0.11132 0.10711 -0.0502 0.0460 1.0000
12.500 0.9891 0.11925 0.11497 -0.0538 0.0469 1.0000
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Polar data table (+)
Polar graphs
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