AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 500,000 Max Cl/Cd: 91.8 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag26-il-500000.txt Download as CSV file: xf-ag26-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4872 0.09523 0.09305 -0.0012 1.0000 0.0124
-8.000 -0.4952 0.08860 0.08647 -0.0040 1.0000 0.0129
-7.750 -0.4907 0.08526 0.08316 -0.0054 1.0000 0.0133
-7.500 -0.4845 0.08206 0.07998 -0.0074 1.0000 0.0136
-7.250 -0.4746 0.07843 0.07636 -0.0107 1.0000 0.0140
-7.000 -0.4627 0.07432 0.07225 -0.0153 1.0000 0.0146
-6.750 -0.4482 0.06962 0.06754 -0.0212 1.0000 0.0153
-6.500 -0.4305 0.06418 0.06209 -0.0284 1.0000 0.0163
-6.250 -0.4078 0.05761 0.05546 -0.0370 1.0000 0.0177
-6.000 -0.3744 0.05109 0.04879 -0.0450 1.0000 0.0193
-5.750 -0.3524 0.04518 0.04266 -0.0495 1.0000 0.0195
-4.250 -0.2231 0.01506 0.00996 -0.0563 1.0000 0.0136
-4.000 -0.1898 0.01336 0.00797 -0.0572 0.9986 0.0131
-3.750 -0.1525 0.01158 0.00597 -0.0591 0.9964 0.0138
-3.500 -0.1144 0.01065 0.00495 -0.0613 0.9938 0.0157
-3.250 -0.0774 0.00995 0.00417 -0.0631 0.9896 0.0180
-3.000 -0.0391 0.00914 0.00328 -0.0653 0.9858 0.0229
-2.750 0.0005 0.00851 0.00260 -0.0676 0.9824 0.0340
-2.500 0.0353 0.00793 0.00218 -0.0690 0.9747 0.0786
-2.250 0.0706 0.00742 0.00195 -0.0707 0.9672 0.1569
-2.000 0.1022 0.00697 0.00180 -0.0716 0.9556 0.2515
-1.750 0.1310 0.00661 0.00169 -0.0717 0.9415 0.3414
-1.500 0.1578 0.00633 0.00160 -0.0713 0.9251 0.4225
-1.250 0.1836 0.00607 0.00154 -0.0706 0.9070 0.5031
-1.000 0.2090 0.00581 0.00149 -0.0698 0.8886 0.5944
-0.750 0.2333 0.00545 0.00146 -0.0687 0.8694 0.7147
-0.500 0.2512 0.00488 0.00140 -0.0657 0.8495 0.9331
-0.250 0.2825 0.00491 0.00130 -0.0661 0.8291 1.0000
0.000 0.3096 0.00500 0.00126 -0.0657 0.8075 1.0000
0.250 0.3368 0.00510 0.00122 -0.0653 0.7860 1.0000
0.500 0.3641 0.00521 0.00120 -0.0650 0.7637 1.0000
0.750 0.3914 0.00533 0.00119 -0.0647 0.7409 1.0000
1.000 0.4188 0.00546 0.00120 -0.0644 0.7178 1.0000
1.250 0.4461 0.00560 0.00122 -0.0642 0.6940 1.0000
1.500 0.4736 0.00574 0.00126 -0.0639 0.6692 1.0000
1.750 0.5009 0.00590 0.00130 -0.0637 0.6430 1.0000
2.000 0.5282 0.00608 0.00136 -0.0635 0.6152 1.0000
2.250 0.5553 0.00628 0.00143 -0.0632 0.5856 1.0000
2.500 0.5824 0.00649 0.00151 -0.0630 0.5546 1.0000
2.750 0.6096 0.00671 0.00163 -0.0628 0.5226 1.0000
3.000 0.6366 0.00696 0.00174 -0.0626 0.4885 1.0000
3.250 0.6635 0.00723 0.00188 -0.0625 0.4546 1.0000
3.500 0.6903 0.00752 0.00203 -0.0623 0.4187 1.0000
3.750 0.7171 0.00782 0.00223 -0.0621 0.3847 1.0000
4.000 0.7438 0.00815 0.00242 -0.0620 0.3506 1.0000
4.250 0.7703 0.00849 0.00264 -0.0618 0.3175 1.0000
4.500 0.7969 0.00883 0.00287 -0.0616 0.2879 1.0000
4.750 0.8234 0.00919 0.00315 -0.0615 0.2570 1.0000
5.000 0.8498 0.00956 0.00342 -0.0613 0.2297 1.0000
5.250 0.8759 0.00996 0.00372 -0.0611 0.2008 1.0000
5.500 0.9020 0.01038 0.00405 -0.0609 0.1739 1.0000
5.750 0.9278 0.01084 0.00440 -0.0607 0.1469 1.0000
6.000 0.9535 0.01132 0.00481 -0.0604 0.1230 1.0000
6.250 0.9788 0.01185 0.00525 -0.0602 0.1021 1.0000
6.500 1.0044 0.01232 0.00569 -0.0599 0.0853 1.0000
6.750 1.0297 0.01282 0.00615 -0.0596 0.0702 1.0000
7.000 1.0547 0.01337 0.00665 -0.0592 0.0565 1.0000
7.250 1.0794 0.01396 0.00721 -0.0589 0.0437 1.0000
7.500 1.1035 0.01469 0.00793 -0.0584 0.0316 1.0000
7.750 1.1269 0.01553 0.00877 -0.0578 0.0219 1.0000
8.000 1.1504 0.01632 0.00965 -0.0572 0.0168 1.0000
8.250 1.1702 0.01786 0.01132 -0.0560 0.0129 1.0000
8.500 1.1935 0.01859 0.01215 -0.0554 0.0110 1.0000
8.750 1.2155 0.01948 0.01310 -0.0547 0.0093 1.0000
9.000 1.2282 0.02205 0.01591 -0.0528 0.0081 1.0000
9.250 1.2489 0.02310 0.01711 -0.0519 0.0077 1.0000
9.500 1.2673 0.02449 0.01870 -0.0507 0.0072 1.0000
9.750 1.2841 0.02608 0.02048 -0.0494 0.0067 1.0000
10.000 1.2994 0.02781 0.02240 -0.0480 0.0063 1.0000
10.250 1.3131 0.02965 0.02443 -0.0465 0.0060 1.0000
10.500 1.3242 0.03170 0.02669 -0.0448 0.0057 1.0000
10.750 1.3319 0.03402 0.02923 -0.0430 0.0056 1.0000
11.000 1.3351 0.03667 0.03212 -0.0408 0.0054 1.0000
11.250 1.3317 0.03947 0.03518 -0.0381 0.0054 1.0000
11.500 1.3228 0.04248 0.03843 -0.0354 0.0054 1.0000
11.750 1.3110 0.04608 0.04228 -0.0339 0.0054 1.0000
12.000 1.2971 0.05044 0.04689 -0.0338 0.0054 1.0000
12.250 1.2811 0.05574 0.05244 -0.0352 0.0055 1.0000
12.500 1.2628 0.06221 0.05916 -0.0384 0.0055 1.0000
12.750 1.2428 0.06981 0.06699 -0.0430 0.0056 1.0000
13.000 1.2210 0.07854 0.07593 -0.0487 0.0057 1.0000
13.250 1.1979 0.08821 0.08579 -0.0550 0.0058 1.0000
13.500 1.1740 0.09851 0.09624 -0.0614 0.0059 1.0000
13.750 1.1478 0.10984 0.10771 -0.0681 0.0060 1.0000
14.000 1.1160 0.12311 0.12112 -0.0755 0.0062 1.0000
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Polar data table (+)
Polar graphs
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