AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 50,000 Max Cl/Cd: 38.28 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag24-il-50000-n5.txt Download as CSV file: xf-ag24-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5002 0.10336 0.09645 -0.0121 1.0000 0.0470
-8.750 -0.4948 0.09944 0.09258 -0.0129 1.0000 0.0460
-8.500 -0.4916 0.09533 0.08852 -0.0146 1.0000 0.0451
-8.250 -0.4896 0.09108 0.08434 -0.0168 1.0000 0.0442
-8.000 -0.4888 0.08667 0.08001 -0.0194 1.0000 0.0434
-7.750 -0.4876 0.08184 0.07525 -0.0232 1.0000 0.0426
-7.500 -0.4842 0.07612 0.06959 -0.0288 1.0000 0.0417
-7.250 -0.4796 0.06960 0.06306 -0.0352 1.0000 0.0407
-7.000 -0.4749 0.06296 0.05631 -0.0410 1.0000 0.0398
-6.750 -0.4679 0.05674 0.04987 -0.0456 1.0000 0.0392
-6.500 -0.4575 0.05102 0.04379 -0.0491 1.0000 0.0388
-6.250 -0.4431 0.04653 0.03895 -0.0510 1.0000 0.0395
-6.000 -0.4260 0.04278 0.03482 -0.0522 1.0000 0.0415
-5.750 -0.4065 0.03902 0.03053 -0.0532 1.0000 0.0439
-5.500 -0.3847 0.03546 0.02635 -0.0536 1.0000 0.0458
-5.250 -0.3613 0.03236 0.02264 -0.0535 1.0000 0.0471
-5.000 -0.3379 0.02970 0.01961 -0.0530 1.0000 0.0490
-4.750 -0.3152 0.02792 0.01765 -0.0526 1.0000 0.0542
-4.500 -0.2908 0.02623 0.01556 -0.0518 1.0000 0.0611
-4.250 -0.2678 0.02457 0.01388 -0.0510 1.0000 0.0673
-4.000 -0.2441 0.02323 0.01244 -0.0503 1.0000 0.0799
-3.750 -0.2199 0.02192 0.01105 -0.0497 1.0000 0.0979
-3.500 -0.1949 0.02061 0.00990 -0.0496 1.0000 0.1376
-3.250 -0.1689 0.01924 0.00896 -0.0501 1.0000 0.2271
-3.000 -0.1443 0.01833 0.00855 -0.0500 1.0000 0.3495
-2.750 -0.1214 0.01775 0.00832 -0.0492 1.0000 0.4558
-2.500 -0.0998 0.01731 0.00814 -0.0478 1.0000 0.5470
-2.250 -0.0801 0.01694 0.00799 -0.0458 1.0000 0.6299
-2.000 -0.0630 0.01662 0.00782 -0.0431 1.0000 0.7117
-1.750 -0.0482 0.01631 0.00766 -0.0398 1.0000 0.8025
-1.250 -0.0015 0.01603 0.00712 -0.0389 1.0000 1.0000
-1.000 0.0241 0.01624 0.00704 -0.0395 1.0000 1.0000
-0.750 0.0694 0.01652 0.00699 -0.0437 0.9877 1.0000
-0.500 0.1141 0.01679 0.00701 -0.0477 0.9747 1.0000
-0.250 0.1578 0.01704 0.00706 -0.0514 0.9609 1.0000
0.000 0.2010 0.01726 0.00711 -0.0547 0.9469 1.0000
0.250 0.2437 0.01745 0.00718 -0.0579 0.9326 1.0000
0.500 0.2848 0.01760 0.00725 -0.0605 0.9175 1.0000
0.750 0.3237 0.01772 0.00730 -0.0626 0.9017 1.0000
1.000 0.3612 0.01781 0.00735 -0.0642 0.8855 1.0000
1.250 0.3937 0.01791 0.00743 -0.0648 0.8664 1.0000
1.500 0.4265 0.01799 0.00752 -0.0654 0.8477 1.0000
1.750 0.4588 0.01804 0.00756 -0.0656 0.8291 1.0000
2.000 0.4874 0.01815 0.00767 -0.0652 0.8074 1.0000
2.250 0.5171 0.01821 0.00773 -0.0648 0.7871 1.0000
2.500 0.5442 0.01833 0.00791 -0.0641 0.7639 1.0000
2.750 0.5713 0.01845 0.00804 -0.0633 0.7407 1.0000
3.000 0.5984 0.01857 0.00815 -0.0624 0.7174 1.0000
3.250 0.6243 0.01875 0.00835 -0.0614 0.6920 1.0000
3.500 0.6500 0.01897 0.00862 -0.0603 0.6658 1.0000
3.750 0.6754 0.01921 0.00888 -0.0593 0.6390 1.0000
4.000 0.7007 0.01949 0.00916 -0.0583 0.6114 1.0000
4.250 0.7260 0.01981 0.00950 -0.0573 0.5832 1.0000
4.500 0.7509 0.02018 0.00993 -0.0563 0.5544 1.0000
4.750 0.7756 0.02059 0.01035 -0.0553 0.5252 1.0000
5.000 0.8000 0.02105 0.01082 -0.0543 0.4956 1.0000
5.250 0.8240 0.02157 0.01136 -0.0534 0.4651 1.0000
5.500 0.8476 0.02214 0.01198 -0.0524 0.4339 1.0000
5.750 0.8708 0.02276 0.01269 -0.0515 0.4024 1.0000
6.000 0.8934 0.02344 0.01339 -0.0505 0.3709 1.0000
6.250 0.9155 0.02419 0.01418 -0.0495 0.3384 1.0000
6.500 0.9368 0.02502 0.01505 -0.0485 0.3052 1.0000
6.750 0.9572 0.02594 0.01596 -0.0475 0.2724 1.0000
7.000 0.9770 0.02698 0.01704 -0.0465 0.2378 1.0000
7.250 0.9954 0.02816 0.01826 -0.0454 0.2048 1.0000
7.500 1.0130 0.02953 0.01963 -0.0444 0.1718 1.0000
7.750 1.0293 0.03112 0.02120 -0.0432 0.1413 1.0000
8.000 1.0442 0.03291 0.02296 -0.0420 0.1145 1.0000
8.250 1.0580 0.03495 0.02495 -0.0407 0.0949 1.0000
8.500 1.0719 0.03706 0.02718 -0.0394 0.0781 1.0000
8.750 1.0851 0.03938 0.02959 -0.0379 0.0670 1.0000
9.000 1.0961 0.04166 0.03189 -0.0366 0.0581 1.0000
9.250 1.1108 0.04438 0.03500 -0.0350 0.0520 1.0000
9.500 1.1206 0.04700 0.03766 -0.0337 0.0472 1.0000
9.750 1.1299 0.05003 0.04123 -0.0322 0.0428 1.0000
10.000 1.1362 0.05315 0.04468 -0.0308 0.0400 1.0000
10.250 1.1398 0.05646 0.04825 -0.0294 0.0383 1.0000
10.500 1.1393 0.05982 0.05180 -0.0279 0.0370 1.0000
10.750 1.1348 0.06374 0.05586 -0.0267 0.0360 1.0000
11.000 1.1224 0.06797 0.06047 -0.0261 0.0356 1.0000
11.250 1.1075 0.07273 0.06554 -0.0266 0.0354 1.0000
11.500 1.0909 0.07812 0.07120 -0.0283 0.0353 1.0000
11.750 1.0729 0.08425 0.07756 -0.0313 0.0354 1.0000
12.000 1.0547 0.09106 0.08455 -0.0351 0.0356 1.0000
12.250 1.0369 0.09846 0.09207 -0.0396 0.0359 1.0000
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Polar data table (+)
Polar graphs
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