AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 50,000 Max Cl/Cd: 38.95 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag25-il-50000-n5.txt Download as CSV file: xf-ag25-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3923 0.09154 0.08510 -0.0181 1.0000 0.0525
-8.250 -0.4920 0.09819 0.09155 -0.0158 1.0000 0.0539
-8.000 -0.4786 0.09452 0.08782 -0.0130 1.0000 0.0516
-7.750 -0.4737 0.09062 0.08397 -0.0143 1.0000 0.0497
-7.500 -0.4696 0.08634 0.07976 -0.0171 1.0000 0.0478
-7.250 -0.4640 0.08134 0.07483 -0.0217 1.0000 0.0459
-6.750 -0.4447 0.06627 0.05958 -0.0399 1.0000 0.0407
-6.500 -0.4334 0.06150 0.05473 -0.0427 1.0000 0.0402
-6.250 -0.4203 0.05651 0.04959 -0.0459 1.0000 0.0398
-6.000 -0.4048 0.05148 0.04431 -0.0490 1.0000 0.0395
-5.750 -0.3868 0.04660 0.03907 -0.0516 1.0000 0.0393
-5.500 -0.3662 0.04200 0.03394 -0.0537 1.0000 0.0394
-5.250 -0.3433 0.03785 0.02920 -0.0551 1.0000 0.0399
-5.000 -0.3198 0.03436 0.02520 -0.0559 1.0000 0.0422
-4.750 -0.2972 0.03215 0.02280 -0.0561 1.0000 0.0462
-4.500 -0.2718 0.02953 0.01970 -0.0560 1.0000 0.0489
-4.250 -0.2458 0.02716 0.01684 -0.0555 1.0000 0.0515
-4.000 -0.2210 0.02524 0.01468 -0.0550 1.0000 0.0565
-3.750 -0.1961 0.02388 0.01305 -0.0543 1.0000 0.0662
-3.500 -0.1718 0.02236 0.01145 -0.0536 1.0000 0.0752
-3.250 -0.1468 0.02116 0.01019 -0.0532 1.0000 0.0964
-3.000 -0.1200 0.01984 0.00897 -0.0532 1.0000 0.1364
-2.750 -0.0927 0.01844 0.00814 -0.0538 1.0000 0.2434
-2.500 -0.0678 0.01750 0.00781 -0.0537 1.0000 0.3922
-2.250 -0.0455 0.01685 0.00760 -0.0526 1.0000 0.5211
-2.000 -0.0264 0.01629 0.00737 -0.0503 1.0000 0.6377
-1.750 -0.0123 0.01573 0.00717 -0.0466 1.0000 0.7665
-1.500 0.0070 0.01525 0.00676 -0.0445 1.0000 1.0000
-1.250 0.0336 0.01540 0.00653 -0.0451 1.0000 1.0000
-1.000 0.0593 0.01558 0.00641 -0.0454 1.0000 1.0000
-0.750 0.0845 0.01581 0.00634 -0.0457 1.0000 1.0000
-0.500 0.1139 0.01608 0.00638 -0.0468 0.9969 1.0000
-0.250 0.1598 0.01638 0.00645 -0.0510 0.9833 1.0000
0.000 0.2051 0.01665 0.00652 -0.0549 0.9690 1.0000
0.250 0.2488 0.01688 0.00661 -0.0584 0.9538 1.0000
0.500 0.2914 0.01708 0.00671 -0.0614 0.9377 1.0000
0.750 0.3324 0.01724 0.00680 -0.0640 0.9207 1.0000
1.000 0.3716 0.01735 0.00688 -0.0660 0.9031 1.0000
1.250 0.4092 0.01744 0.00694 -0.0676 0.8850 1.0000
1.500 0.4420 0.01753 0.00706 -0.0681 0.8639 1.0000
1.750 0.4756 0.01759 0.00711 -0.0686 0.8438 1.0000
2.000 0.5053 0.01768 0.00721 -0.0683 0.8205 1.0000
2.250 0.5343 0.01777 0.00731 -0.0678 0.7969 1.0000
2.500 0.5626 0.01787 0.00741 -0.0671 0.7726 1.0000
2.750 0.5899 0.01798 0.00757 -0.0661 0.7472 1.0000
3.000 0.6162 0.01813 0.00773 -0.0650 0.7201 1.0000
3.250 0.6419 0.01832 0.00790 -0.0639 0.6919 1.0000
3.500 0.6671 0.01856 0.00814 -0.0627 0.6620 1.0000
3.750 0.6921 0.01883 0.00847 -0.0615 0.6312 1.0000
4.000 0.7168 0.01914 0.00877 -0.0603 0.5999 1.0000
4.250 0.7414 0.01949 0.00910 -0.0591 0.5682 1.0000
4.500 0.7659 0.01992 0.00952 -0.0581 0.5348 1.0000
4.750 0.7902 0.02039 0.00998 -0.0570 0.5016 1.0000
5.000 0.8142 0.02092 0.01056 -0.0560 0.4681 1.0000
5.250 0.8378 0.02151 0.01117 -0.0551 0.4339 1.0000
5.500 0.8611 0.02216 0.01180 -0.0541 0.4004 1.0000
5.750 0.8841 0.02287 0.01255 -0.0532 0.3659 1.0000
6.000 0.9064 0.02366 0.01332 -0.0522 0.3328 1.0000
6.250 0.9285 0.02452 0.01430 -0.0513 0.2987 1.0000
6.500 0.9498 0.02547 0.01526 -0.0504 0.2659 1.0000
6.750 0.9705 0.02653 0.01633 -0.0495 0.2333 1.0000
7.000 0.9905 0.02770 0.01754 -0.0486 0.2012 1.0000
7.250 1.0095 0.02903 0.01886 -0.0476 0.1712 1.0000
7.500 1.0277 0.03055 0.02039 -0.0466 0.1439 1.0000
7.750 1.0449 0.03222 0.02209 -0.0455 0.1185 1.0000
8.000 1.0613 0.03415 0.02414 -0.0443 0.0987 1.0000
8.250 1.0769 0.03620 0.02632 -0.0431 0.0818 1.0000
8.500 1.0919 0.03845 0.02871 -0.0417 0.0692 1.0000
8.750 1.1058 0.04085 0.03127 -0.0404 0.0594 1.0000
9.000 1.1194 0.04343 0.03396 -0.0391 0.0532 1.0000
9.250 1.1316 0.04642 0.03736 -0.0376 0.0471 1.0000
9.500 1.1408 0.04904 0.04018 -0.0364 0.0425 1.0000
9.750 1.1490 0.05261 0.04389 -0.0350 0.0402 1.0000
10.000 1.1513 0.05672 0.04858 -0.0335 0.0388 1.0000
10.250 1.1469 0.06090 0.05325 -0.0321 0.0375 1.0000
10.500 1.1360 0.06497 0.05768 -0.0308 0.0366 1.0000
10.750 1.1215 0.06943 0.06243 -0.0304 0.0361 1.0000
11.000 1.1040 0.07461 0.06788 -0.0315 0.0359 1.0000
11.250 1.0842 0.08078 0.07428 -0.0343 0.0363 1.0000
11.500 1.0630 0.08807 0.08176 -0.0386 0.0370 1.0000
11.750 1.0420 0.09630 0.09012 -0.0441 0.0379 1.0000
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Polar data table (+)
Polar graphs
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