AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 100,000 Max Cl/Cd: 52.69 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag24-il-100000-n5.txt Download as CSV file: xf-ag24-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4983 0.08982 0.08499 -0.0130 1.0000 0.0225
-8.250 -0.4976 0.08527 0.08050 -0.0158 1.0000 0.0221
-8.000 -0.4978 0.08050 0.07580 -0.0190 1.0000 0.0217
-7.750 -0.4976 0.07513 0.07050 -0.0237 1.0000 0.0213
-7.500 -0.4937 0.06813 0.06352 -0.0316 1.0000 0.0208
-7.250 -0.4882 0.05954 0.05485 -0.0405 1.0000 0.0203
-7.000 -0.4824 0.05164 0.04670 -0.0468 1.0000 0.0198
-6.750 -0.4734 0.04493 0.03959 -0.0508 1.0000 0.0195
-6.500 -0.4594 0.04020 0.03445 -0.0527 1.0000 0.0201
-6.250 -0.4424 0.03635 0.03015 -0.0536 1.0000 0.0215
-6.000 -0.4232 0.03275 0.02601 -0.0541 1.0000 0.0228
-5.750 -0.4021 0.02951 0.02220 -0.0541 1.0000 0.0236
-5.500 -0.3795 0.02676 0.01894 -0.0537 1.0000 0.0241
-5.250 -0.3560 0.02458 0.01633 -0.0532 1.0000 0.0249
-5.000 -0.3326 0.02234 0.01383 -0.0527 1.0000 0.0261
-4.750 -0.3095 0.02096 0.01237 -0.0523 1.0000 0.0288
-4.500 -0.2856 0.01995 0.01116 -0.0517 1.0000 0.0332
-4.250 -0.2612 0.01878 0.00983 -0.0511 1.0000 0.0361
-4.000 -0.2367 0.01762 0.00865 -0.0509 1.0000 0.0417
-3.750 -0.2117 0.01679 0.00776 -0.0506 1.0000 0.0520
-3.500 -0.1858 0.01596 0.00692 -0.0506 1.0000 0.0691
-3.250 -0.1593 0.01510 0.00623 -0.0508 1.0000 0.1125
-3.000 -0.1323 0.01431 0.00586 -0.0514 0.9997 0.2014
-2.750 -0.0937 0.01367 0.00563 -0.0542 0.9932 0.3160
-2.500 -0.0560 0.01324 0.00548 -0.0565 0.9854 0.4119
-2.250 -0.0189 0.01291 0.00533 -0.0585 0.9773 0.4958
-2.000 0.0192 0.01262 0.00522 -0.0604 0.9696 0.5737
-1.750 0.0534 0.01237 0.00513 -0.0614 0.9596 0.6456
-1.500 0.0855 0.01214 0.00505 -0.0617 0.9491 0.7161
-1.250 0.1156 0.01192 0.00493 -0.0614 0.9380 0.7865
-1.000 0.1443 0.01170 0.00478 -0.0607 0.9262 0.8595
-0.750 0.1827 0.01144 0.00453 -0.0621 0.9140 0.9617
-0.500 0.2176 0.01139 0.00432 -0.0634 0.8997 1.0000
-0.250 0.2491 0.01139 0.00419 -0.0640 0.8846 1.0000
0.000 0.2793 0.01141 0.00410 -0.0642 0.8683 1.0000
0.250 0.3087 0.01143 0.00402 -0.0643 0.8514 1.0000
0.500 0.3376 0.01147 0.00395 -0.0642 0.8339 1.0000
0.750 0.3662 0.01150 0.00388 -0.0639 0.8162 1.0000
1.000 0.3937 0.01157 0.00387 -0.0635 0.7963 1.0000
1.250 0.4212 0.01164 0.00387 -0.0631 0.7763 1.0000
1.500 0.4484 0.01174 0.00388 -0.0626 0.7551 1.0000
1.750 0.4754 0.01184 0.00390 -0.0621 0.7333 1.0000
2.000 0.5022 0.01198 0.00396 -0.0616 0.7099 1.0000
2.250 0.5289 0.01213 0.00403 -0.0610 0.6861 1.0000
2.500 0.5555 0.01231 0.00415 -0.0605 0.6616 1.0000
2.750 0.5819 0.01251 0.00427 -0.0599 0.6360 1.0000
3.000 0.6083 0.01273 0.00442 -0.0594 0.6096 1.0000
3.250 0.6345 0.01298 0.00460 -0.0589 0.5830 1.0000
3.500 0.6606 0.01325 0.00484 -0.0584 0.5560 1.0000
3.750 0.6865 0.01356 0.00508 -0.0579 0.5287 1.0000
4.000 0.7124 0.01388 0.00535 -0.0574 0.5010 1.0000
4.250 0.7380 0.01423 0.00565 -0.0569 0.4734 1.0000
4.500 0.7636 0.01461 0.00602 -0.0564 0.4455 1.0000
4.750 0.7889 0.01502 0.00639 -0.0559 0.4173 1.0000
5.000 0.8140 0.01545 0.00679 -0.0555 0.3887 1.0000
5.250 0.8389 0.01592 0.00723 -0.0550 0.3597 1.0000
5.500 0.8635 0.01643 0.00775 -0.0545 0.3303 1.0000
5.750 0.8877 0.01699 0.00827 -0.0540 0.3004 1.0000
6.000 0.9118 0.01758 0.00884 -0.0534 0.2700 1.0000
6.250 0.9354 0.01822 0.00947 -0.0529 0.2389 1.0000
6.500 0.9586 0.01894 0.01015 -0.0524 0.2076 1.0000
6.750 0.9811 0.01976 0.01090 -0.0518 0.1770 1.0000
7.000 1.0033 0.02064 0.01179 -0.0512 0.1460 1.0000
7.250 1.0247 0.02164 0.01274 -0.0506 0.1156 1.0000
7.500 1.0451 0.02281 0.01383 -0.0498 0.0880 1.0000
7.750 1.0644 0.02415 0.01511 -0.0490 0.0659 1.0000
8.000 1.0825 0.02563 0.01659 -0.0479 0.0503 1.0000
8.250 1.0996 0.02719 0.01823 -0.0467 0.0398 1.0000
8.500 1.1150 0.02894 0.02008 -0.0454 0.0332 1.0000
8.750 1.1303 0.03063 0.02193 -0.0440 0.0287 1.0000
9.000 1.1426 0.03265 0.02411 -0.0424 0.0251 1.0000
9.250 1.1571 0.03444 0.02616 -0.0410 0.0223 1.0000
9.500 1.1693 0.03653 0.02844 -0.0393 0.0206 1.0000
9.750 1.1800 0.03873 0.03082 -0.0378 0.0194 1.0000
10.000 1.1877 0.04131 0.03356 -0.0361 0.0183 1.0000
10.250 1.1928 0.04439 0.03688 -0.0343 0.0174 1.0000
10.500 1.1969 0.04684 0.03968 -0.0323 0.0164 1.0000
10.750 1.1966 0.04955 0.04271 -0.0304 0.0156 1.0000
11.000 1.1930 0.05255 0.04601 -0.0288 0.0149 1.0000
11.250 1.1861 0.05601 0.04975 -0.0278 0.0145 1.0000
11.500 1.1764 0.06002 0.05403 -0.0276 0.0143 1.0000
11.750 1.1640 0.06464 0.05893 -0.0283 0.0142 1.0000
12.000 1.1495 0.06994 0.06449 -0.0302 0.0141 1.0000
12.250 1.1331 0.07604 0.07084 -0.0332 0.0142 1.0000
12.500 1.1144 0.08315 0.07817 -0.0374 0.0142 1.0000
12.750 1.0936 0.09135 0.08659 -0.0427 0.0144 1.0000
13.000 1.0710 0.10074 0.09616 -0.0490 0.0147 1.0000
13.250 1.0459 0.11150 0.10707 -0.0560 0.0152 1.0000
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Polar data table (+)
Polar graphs
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