AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 500,000 Max Cl/Cd: 82.96 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag26-il-500000-n5.txt Download as CSV file: xf-ag26-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5193 0.11287 0.11059 0.0113 1.0000 0.0065
-9.250 -0.5158 0.10880 0.10653 0.0096 1.0000 0.0060
-9.000 -0.5134 0.10425 0.10201 0.0076 1.0000 0.0055
-8.750 -0.5123 0.09920 0.09698 0.0052 1.0000 0.0052
-8.500 -0.5109 0.09436 0.09216 0.0026 1.0000 0.0050
-8.250 -0.5072 0.09043 0.08825 0.0004 1.0000 0.0051
-8.000 -0.5037 0.08641 0.08426 -0.0020 1.0000 0.0052
-7.750 -0.5003 0.08232 0.08020 -0.0049 1.0000 0.0052
-7.500 -0.4941 0.07783 0.07573 -0.0091 1.0000 0.0053
-7.250 -0.4836 0.07255 0.07047 -0.0154 1.0000 0.0054
-7.000 -0.4696 0.06649 0.06440 -0.0231 1.0000 0.0055
-6.750 -0.4518 0.05916 0.05703 -0.0326 1.0000 0.0056
-6.500 -0.4300 0.05046 0.04822 -0.0427 1.0000 0.0056
-6.250 -0.4072 0.04173 0.03927 -0.0505 1.0000 0.0059
-6.000 -0.3855 0.03238 0.02948 -0.0555 1.0000 0.0063
-5.750 -0.3635 0.02366 0.02001 -0.0582 1.0000 0.0063
-5.500 -0.3374 0.01870 0.01434 -0.0593 0.9993 0.0062
-5.250 -0.3034 0.01580 0.01091 -0.0612 0.9959 0.0062
-5.000 -0.2696 0.01395 0.00868 -0.0626 0.9924 0.0064
-4.750 -0.2366 0.01262 0.00710 -0.0638 0.9874 0.0066
-4.500 -0.2025 0.01159 0.00590 -0.0652 0.9825 0.0071
-4.250 -0.1705 0.01087 0.00505 -0.0660 0.9753 0.0076
-4.000 -0.1371 0.01001 0.00407 -0.0672 0.9682 0.0086
-3.750 -0.1058 0.00957 0.00355 -0.0679 0.9576 0.0097
-3.500 -0.0751 0.00926 0.00319 -0.0684 0.9455 0.0115
-3.250 -0.0456 0.00886 0.00271 -0.0685 0.9316 0.0144
-3.000 -0.0174 0.00857 0.00236 -0.0684 0.9159 0.0184
-2.750 0.0098 0.00832 0.00207 -0.0680 0.8989 0.0270
-2.500 0.0368 0.00810 0.00183 -0.0676 0.8804 0.0438
-2.250 0.0636 0.00788 0.00164 -0.0672 0.8610 0.0719
-2.000 0.0904 0.00768 0.00149 -0.0669 0.8406 0.1093
-1.750 0.1174 0.00749 0.00135 -0.0666 0.8195 0.1558
-1.500 0.1445 0.00729 0.00124 -0.0664 0.7980 0.2159
-1.250 0.1716 0.00713 0.00116 -0.0662 0.7761 0.2770
-1.000 0.1989 0.00700 0.00111 -0.0661 0.7539 0.3377
-0.750 0.2262 0.00690 0.00107 -0.0659 0.7318 0.3957
-0.500 0.2536 0.00681 0.00104 -0.0657 0.7090 0.4531
-0.250 0.2809 0.00673 0.00104 -0.0656 0.6861 0.5122
0.000 0.3081 0.00665 0.00104 -0.0654 0.6629 0.5774
0.250 0.3349 0.00651 0.00107 -0.0651 0.6393 0.6616
0.500 0.3590 0.00620 0.00111 -0.0641 0.6166 0.8001
0.750 0.3845 0.00595 0.00107 -0.0631 0.5928 1.0000
1.250 0.4399 0.00626 0.00113 -0.0629 0.5436 1.0000
1.500 0.4675 0.00643 0.00118 -0.0628 0.5182 1.0000
1.750 0.4950 0.00663 0.00124 -0.0627 0.4902 1.0000
2.000 0.5224 0.00684 0.00132 -0.0626 0.4605 1.0000
2.250 0.5497 0.00708 0.00141 -0.0625 0.4290 1.0000
2.500 0.5769 0.00733 0.00152 -0.0624 0.3967 1.0000
2.750 0.6041 0.00759 0.00166 -0.0623 0.3659 1.0000
3.000 0.6312 0.00786 0.00181 -0.0622 0.3361 1.0000
3.250 0.6584 0.00812 0.00196 -0.0621 0.3091 1.0000
3.500 0.6854 0.00840 0.00213 -0.0620 0.2831 1.0000
3.750 0.7125 0.00868 0.00233 -0.0619 0.2593 1.0000
4.000 0.7394 0.00897 0.00253 -0.0617 0.2366 1.0000
4.250 0.7663 0.00927 0.00275 -0.0616 0.2129 1.0000
4.500 0.7931 0.00956 0.00298 -0.0615 0.1932 1.0000
4.750 0.8196 0.00991 0.00326 -0.0613 0.1699 1.0000
5.000 0.8462 0.01023 0.00353 -0.0612 0.1506 1.0000
5.500 0.8988 0.01099 0.00415 -0.0608 0.1116 1.0000
5.750 0.9249 0.01139 0.00450 -0.0606 0.0953 1.0000
6.000 0.9509 0.01179 0.00489 -0.0604 0.0814 1.0000
6.250 0.9767 0.01221 0.00527 -0.0602 0.0689 1.0000
6.500 1.0024 0.01265 0.00569 -0.0599 0.0570 1.0000
6.750 1.0278 0.01311 0.00613 -0.0596 0.0461 1.0000
7.000 1.0530 0.01361 0.00661 -0.0593 0.0363 1.0000
7.250 1.0780 0.01414 0.00713 -0.0590 0.0279 1.0000
7.500 1.1025 0.01473 0.00774 -0.0586 0.0205 1.0000
7.750 1.1269 0.01533 0.00834 -0.0582 0.0151 1.0000
8.000 1.1511 0.01594 0.00901 -0.0577 0.0116 1.0000
8.250 1.1747 0.01666 0.00977 -0.0572 0.0090 1.0000
8.500 1.1980 0.01742 0.01063 -0.0566 0.0075 1.0000
8.750 1.2212 0.01811 0.01142 -0.0561 0.0063 1.0000
9.000 1.2432 0.01899 0.01236 -0.0554 0.0052 1.0000
9.250 1.2648 0.01992 0.01345 -0.0547 0.0045 1.0000
9.500 1.2862 0.02081 0.01447 -0.0539 0.0041 1.0000
9.750 1.3068 0.02178 0.01558 -0.0531 0.0038 1.0000
10.000 1.3267 0.02281 0.01674 -0.0522 0.0035 1.0000
10.250 1.3457 0.02389 0.01795 -0.0513 0.0032 1.0000
10.500 1.3631 0.02513 0.01933 -0.0502 0.0030 1.0000
10.750 1.3770 0.02676 0.02114 -0.0488 0.0028 1.0000
11.000 1.3856 0.02895 0.02354 -0.0469 0.0026 1.0000
11.250 1.3974 0.03052 0.02531 -0.0454 0.0025 1.0000
11.500 1.4063 0.03228 0.02726 -0.0437 0.0025 1.0000
11.750 1.4108 0.03421 0.02940 -0.0415 0.0024 1.0000
12.000 1.4092 0.03631 0.03173 -0.0389 0.0024 1.0000
12.250 1.4049 0.03881 0.03443 -0.0369 0.0023 1.0000
12.500 1.3983 0.04186 0.03768 -0.0358 0.0023 1.0000
12.750 1.3901 0.04557 0.04160 -0.0358 0.0022 1.0000
13.000 1.3797 0.05010 0.04634 -0.0370 0.0022 1.0000
13.250 1.3676 0.05549 0.05193 -0.0394 0.0022 1.0000
13.500 1.3533 0.06186 0.05851 -0.0429 0.0022 1.0000
13.750 1.3364 0.06923 0.06607 -0.0473 0.0022 1.0000
14.000 1.3172 0.07745 0.07445 -0.0522 0.0022 1.0000
14.250 1.2961 0.08627 0.08344 -0.0572 0.0022 1.0000
14.500 1.2735 0.09550 0.09280 -0.0622 0.0023 1.0000
14.750 1.2498 0.10505 0.10247 -0.0672 0.0023 1.0000
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Polar data table (+)
Polar graphs
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