AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.68 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag26-il-1000000.txt Download as CSV file: xf-ag26-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5803 0.15370 0.15201 0.0287 1.0000 0.0052
-12.000 -0.5743 0.15017 0.14849 0.0274 1.0000 0.0053
-11.750 -0.5684 0.14660 0.14493 0.0260 1.0000 0.0054
-6.500 -0.4246 0.04948 0.04788 -0.0441 1.0000 0.0083
-6.250 -0.4042 0.04501 0.04331 -0.0484 1.0000 0.0086
-6.000 -0.3840 0.04105 0.03923 -0.0512 1.0000 0.0092
-5.750 -0.3637 0.03629 0.03427 -0.0536 1.0000 0.0101
-5.500 -0.3390 0.03371 0.03155 -0.0533 1.0000 0.0121
-5.250 -0.3138 0.02964 0.02717 -0.0549 0.9994 0.0123
-5.000 -0.2779 0.02518 0.02229 -0.0588 0.9970 0.0124
-4.750 -0.2417 0.01283 0.00854 -0.0630 0.9951 0.0083
-4.500 -0.2067 0.01176 0.00729 -0.0645 0.9927 0.0080
-4.250 -0.1723 0.01061 0.00598 -0.0658 0.9893 0.0079
-4.000 -0.1379 0.00905 0.00422 -0.0672 0.9854 0.0081
-3.750 -0.1036 0.00814 0.00318 -0.0685 0.9803 0.0094
-3.500 -0.0721 0.00778 0.00279 -0.0691 0.9715 0.0110
-3.250 -0.0424 0.00751 0.00247 -0.0693 0.9604 0.0122
-3.000 -0.0143 0.00703 0.00190 -0.0691 0.9464 0.0164
-2.750 0.0124 0.00676 0.00160 -0.0685 0.9303 0.0260
-2.500 0.0387 0.00652 0.00137 -0.0680 0.9132 0.0477
-2.250 0.0653 0.00631 0.00122 -0.0675 0.8947 0.0820
-2.000 0.0921 0.00609 0.00109 -0.0672 0.8754 0.1294
-1.750 0.1191 0.00587 0.00098 -0.0670 0.8561 0.1915
-1.500 0.1464 0.00564 0.00090 -0.0668 0.8359 0.2634
-1.250 0.1737 0.00550 0.00085 -0.0667 0.8156 0.3289
-1.000 0.2012 0.00536 0.00081 -0.0666 0.7943 0.3914
-0.750 0.2287 0.00524 0.00079 -0.0664 0.7732 0.4582
-0.500 0.2563 0.00512 0.00077 -0.0663 0.7515 0.5284
-0.250 0.2838 0.00499 0.00078 -0.0662 0.7302 0.6090
0.000 0.3107 0.00478 0.00080 -0.0660 0.7077 0.7166
0.250 0.3326 0.00436 0.00083 -0.0644 0.6865 0.8917
0.500 0.3614 0.00431 0.00079 -0.0643 0.6634 1.0000
0.750 0.3894 0.00443 0.00080 -0.0642 0.6400 1.0000
1.000 0.4173 0.00456 0.00082 -0.0641 0.6160 1.0000
1.250 0.4452 0.00471 0.00085 -0.0640 0.5905 1.0000
1.500 0.4730 0.00487 0.00089 -0.0640 0.5634 1.0000
1.750 0.5007 0.00504 0.00094 -0.0639 0.5345 1.0000
2.000 0.5284 0.00523 0.00100 -0.0638 0.5038 1.0000
2.250 0.5560 0.00543 0.00108 -0.0638 0.4727 1.0000
2.500 0.5835 0.00565 0.00118 -0.0637 0.4408 1.0000
2.750 0.6110 0.00587 0.00127 -0.0636 0.4102 1.0000
3.000 0.6383 0.00612 0.00139 -0.0635 0.3771 1.0000
3.250 0.6657 0.00636 0.00151 -0.0635 0.3484 1.0000
3.500 0.6930 0.00662 0.00165 -0.0634 0.3188 1.0000
3.750 0.7202 0.00688 0.00182 -0.0633 0.2905 1.0000
4.000 0.7474 0.00714 0.00198 -0.0632 0.2656 1.0000
4.250 0.7744 0.00742 0.00215 -0.0631 0.2385 1.0000
4.500 0.8015 0.00768 0.00234 -0.0630 0.2161 1.0000
4.750 0.8284 0.00799 0.00256 -0.0629 0.1910 1.0000
5.000 0.8551 0.00832 0.00279 -0.0628 0.1682 1.0000
5.250 0.8817 0.00866 0.00303 -0.0626 0.1441 1.0000
5.500 0.9082 0.00900 0.00330 -0.0625 0.1230 1.0000
5.750 0.9345 0.00940 0.00360 -0.0623 0.1024 1.0000
6.000 0.9608 0.00976 0.00391 -0.0621 0.0865 1.0000
6.250 0.9870 0.01013 0.00423 -0.0619 0.0722 1.0000
6.500 1.0131 0.01051 0.00456 -0.0617 0.0596 1.0000
6.750 1.0391 0.01091 0.00492 -0.0615 0.0481 1.0000
7.000 1.0648 0.01135 0.00531 -0.0612 0.0374 1.0000
7.250 1.0902 0.01181 0.00574 -0.0610 0.0283 1.0000
7.500 1.1153 0.01234 0.00626 -0.0606 0.0199 1.0000
7.750 1.1399 0.01298 0.00687 -0.0602 0.0130 1.0000
8.000 1.1644 0.01359 0.00748 -0.0598 0.0093 1.0000
8.250 1.1887 0.01424 0.00822 -0.0592 0.0074 1.0000
8.500 1.2129 0.01485 0.00887 -0.0588 0.0062 1.0000
8.750 1.2340 0.01610 0.01028 -0.0578 0.0049 1.0000
9.000 1.2571 0.01685 0.01113 -0.0572 0.0046 1.0000
9.250 1.2802 0.01756 0.01196 -0.0566 0.0043 1.0000
9.500 1.3024 0.01838 0.01287 -0.0559 0.0039 1.0000
9.750 1.3241 0.01924 0.01383 -0.0551 0.0035 1.0000
10.000 1.3446 0.02023 0.01492 -0.0543 0.0032 1.0000
10.250 1.3618 0.02169 0.01653 -0.0531 0.0030 1.0000
10.500 1.3737 0.02386 0.01893 -0.0513 0.0028 1.0000
10.750 1.3809 0.02654 0.02189 -0.0490 0.0027 1.0000
11.000 1.3848 0.02944 0.02508 -0.0465 0.0027 1.0000
11.250 1.3875 0.03217 0.02806 -0.0441 0.0027 1.0000
11.500 1.3854 0.03499 0.03113 -0.0414 0.0027 1.0000
11.750 1.3783 0.03752 0.03385 -0.0383 0.0027 1.0000
12.000 1.3686 0.04051 0.03703 -0.0361 0.0027 1.0000
12.250 1.3562 0.04429 0.04102 -0.0353 0.0027 1.0000
12.500 1.3443 0.04866 0.04558 -0.0359 0.0027 1.0000
12.750 1.3314 0.05387 0.05097 -0.0380 0.0027 1.0000
13.000 1.3177 0.05990 0.05719 -0.0413 0.0027 1.0000
13.250 1.3037 0.06656 0.06400 -0.0454 0.0027 1.0000
13.500 1.2899 0.07369 0.07128 -0.0499 0.0027 1.0000
13.750 1.2760 0.08108 0.07880 -0.0544 0.0027 1.0000
14.000 1.2606 0.08900 0.08684 -0.0591 0.0027 1.0000
14.250 1.2449 0.09700 0.09494 -0.0636 0.0027 1.0000
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