AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 50,000 Max Cl/Cd: 39.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag26-il-50000-n5.txt Download as CSV file: xf-ag26-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG26 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4837 0.10663 0.09986 -0.0009 1.0000 0.1043
-8.000 -0.4918 0.10469 0.09805 -0.0066 1.0000 0.1073
-7.750 -0.4885 0.10088 0.09435 -0.0103 1.0000 0.1080
-7.500 -0.4773 0.09629 0.08977 -0.0095 1.0000 0.1090
-7.000 -0.4529 0.08301 0.07642 -0.0184 1.0000 0.0510
-6.750 -0.4428 0.07848 0.07193 -0.0218 1.0000 0.0487
-6.500 -0.4308 0.07322 0.06667 -0.0271 1.0000 0.0463
-6.000 -0.3939 0.05904 0.05211 -0.0431 1.0000 0.0408
-5.750 -0.3767 0.05430 0.04722 -0.0460 1.0000 0.0403
-5.500 -0.3569 0.04938 0.04204 -0.0492 1.0000 0.0399
-5.250 -0.3346 0.04460 0.03691 -0.0521 1.0000 0.0397
-5.000 -0.3104 0.04010 0.03192 -0.0543 1.0000 0.0398
-4.750 -0.2838 0.03604 0.02720 -0.0560 1.0000 0.0409
-4.500 -0.2603 0.03312 0.02404 -0.0568 1.0000 0.0442
-4.250 -0.2349 0.03066 0.02121 -0.0571 1.0000 0.0477
-4.000 -0.2078 0.02798 0.01801 -0.0572 1.0000 0.0499
-3.750 -0.1807 0.02572 0.01522 -0.0567 1.0000 0.0528
-3.500 -0.1559 0.02413 0.01348 -0.0564 1.0000 0.0608
-3.250 -0.1303 0.02257 0.01167 -0.0556 1.0000 0.0693
-3.000 -0.1051 0.02129 0.01027 -0.0550 1.0000 0.0829
-2.750 -0.0787 0.02012 0.00900 -0.0547 1.0000 0.1075
-2.500 -0.0512 0.01886 0.00798 -0.0550 1.0000 0.1625
-2.250 -0.0241 0.01758 0.00733 -0.0555 1.0000 0.2920
-2.000 -0.0001 0.01664 0.00707 -0.0549 1.0000 0.4634
-1.750 0.0189 0.01580 0.00685 -0.0527 1.0000 0.6290
-1.500 0.0313 0.01479 0.00648 -0.0483 1.0000 1.0000
-1.250 0.0574 0.01492 0.00618 -0.0485 1.0000 1.0000
-1.000 0.0830 0.01508 0.00597 -0.0486 1.0000 1.0000
-0.750 0.1082 0.01527 0.00588 -0.0487 1.0000 1.0000
-0.500 0.1329 0.01551 0.00588 -0.0488 1.0000 1.0000
-0.250 0.1578 0.01579 0.00597 -0.0490 0.9995 1.0000
0.000 0.2035 0.01610 0.00603 -0.0531 0.9844 1.0000
0.250 0.2492 0.01637 0.00615 -0.0571 0.9692 1.0000
0.500 0.2930 0.01660 0.00626 -0.0605 0.9525 1.0000
0.750 0.3363 0.01679 0.00637 -0.0636 0.9351 1.0000
1.000 0.3777 0.01693 0.00647 -0.0661 0.9169 1.0000
1.250 0.4163 0.01704 0.00656 -0.0679 0.8973 1.0000
1.500 0.4516 0.01714 0.00665 -0.0689 0.8757 1.0000
1.750 0.4845 0.01723 0.00677 -0.0692 0.8530 1.0000
2.000 0.5164 0.01730 0.00684 -0.0692 0.8301 1.0000
2.250 0.5451 0.01741 0.00695 -0.0686 0.8047 1.0000
2.500 0.5726 0.01753 0.00708 -0.0677 0.7783 1.0000
2.750 0.5992 0.01768 0.00728 -0.0666 0.7508 1.0000
3.000 0.6252 0.01784 0.00744 -0.0654 0.7223 1.0000
3.250 0.6506 0.01804 0.00762 -0.0641 0.6926 1.0000
3.500 0.6754 0.01829 0.00787 -0.0628 0.6605 1.0000
3.750 0.6999 0.01857 0.00813 -0.0614 0.6273 1.0000
4.000 0.7242 0.01889 0.00850 -0.0601 0.5927 1.0000
4.250 0.7481 0.01927 0.00884 -0.0587 0.5563 1.0000
4.500 0.7719 0.01971 0.00925 -0.0575 0.5179 1.0000
4.750 0.7955 0.02022 0.00971 -0.0563 0.4783 1.0000
5.000 0.8189 0.02080 0.01030 -0.0552 0.4384 1.0000
5.250 0.8419 0.02146 0.01090 -0.0542 0.3988 1.0000
5.500 0.8647 0.02222 0.01158 -0.0532 0.3604 1.0000
5.750 0.8874 0.02305 0.01240 -0.0524 0.3226 1.0000
6.000 0.9096 0.02397 0.01330 -0.0515 0.2868 1.0000
6.250 0.9315 0.02499 0.01437 -0.0507 0.2535 1.0000
6.500 0.9528 0.02612 0.01545 -0.0499 0.2232 1.0000
6.750 0.9740 0.02732 0.01669 -0.0490 0.1942 1.0000
7.000 0.9948 0.02865 0.01805 -0.0482 0.1695 1.0000
7.250 1.0151 0.03005 0.01956 -0.0473 0.1459 1.0000
7.500 1.0347 0.03164 0.02117 -0.0463 0.1271 1.0000
7.750 1.0539 0.03331 0.02302 -0.0454 0.1085 1.0000
8.000 1.0724 0.03523 0.02516 -0.0443 0.0939 1.0000
8.250 1.0893 0.03719 0.02727 -0.0432 0.0802 1.0000
8.500 1.1067 0.03970 0.03004 -0.0420 0.0703 1.0000
8.750 1.1210 0.04202 0.03254 -0.0408 0.0609 1.0000
9.000 1.1355 0.04482 0.03564 -0.0396 0.0547 1.0000
9.250 1.1469 0.04809 0.03922 -0.0383 0.0498 1.0000
9.500 1.1545 0.05122 0.04280 -0.0370 0.0447 1.0000
9.750 1.1613 0.05410 0.04581 -0.0359 0.0416 1.0000
10.000 1.1621 0.05841 0.05047 -0.0345 0.0402 1.0000
10.250 1.1547 0.06308 0.05565 -0.0333 0.0395 1.0000
10.500 1.1410 0.06761 0.06055 -0.0323 0.0391 1.0000
10.750 1.1236 0.07242 0.06564 -0.0324 0.0389 1.0000
11.000 1.1045 0.07794 0.07139 -0.0341 0.0390 1.0000
11.250 1.0848 0.08433 0.07796 -0.0375 0.0393 1.0000
11.500 1.0650 0.09166 0.08543 -0.0423 0.0397 1.0000
11.750 1.0457 0.09983 0.09369 -0.0478 0.0401 1.0000
12.000 1.0280 0.10852 0.10243 -0.0534 0.0405 1.0000
12.250 1.0123 0.11738 0.11130 -0.0588 0.0408 1.0000
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Polar data table (+)
Polar graphs
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