AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 50,000 Max Cl/Cd: 37.78 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag27-il-50000.txt Download as CSV file: xf-ag27-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG27 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4968 0.11030 0.10369 0.0048 1.0000 0.1716
-7.750 -0.4794 0.10466 0.09805 0.0064 1.0000 0.1784
-7.500 -0.4860 0.10355 0.09707 0.0027 1.0000 0.1854
-7.250 -0.4693 0.09829 0.09181 0.0045 1.0000 0.1934
-7.000 -0.4724 0.09640 0.09005 -0.0006 1.0000 0.2009
-6.750 -0.4610 0.09259 0.08627 -0.0002 1.0000 0.2124
-6.500 -0.4493 0.08844 0.08216 0.0004 1.0000 0.2218
-6.250 -0.3611 0.07245 0.06667 -0.0041 1.0000 0.2526
-6.000 -0.3562 0.06877 0.06307 -0.0042 1.0000 0.2660
-5.750 -0.3546 0.06549 0.05988 -0.0053 1.0000 0.2825
-5.500 -0.3489 0.06167 0.05614 -0.0050 1.0000 0.3000
-5.250 -0.3417 0.05822 0.05271 -0.0037 1.0000 0.3242
-5.000 -0.3888 0.06850 0.06258 -0.0056 1.0000 0.3286
-4.750 -0.3781 0.06532 0.05942 -0.0031 1.0000 0.3585
-4.500 -0.3678 0.06233 0.05650 -0.0008 1.0000 0.3914
-4.000 -0.2349 0.04220 0.03483 -0.0512 1.0000 0.1540
-3.750 -0.1945 0.03602 0.02780 -0.0562 1.0000 0.1268
-3.500 -0.1574 0.03164 0.02233 -0.0587 1.0000 0.1167
-3.250 -0.1322 0.02894 0.01961 -0.0586 1.0000 0.1238
-3.000 -0.1010 0.02636 0.01633 -0.0589 1.0000 0.1299
-2.750 -0.0734 0.02405 0.01384 -0.0586 1.0000 0.1392
-2.500 -0.0461 0.02228 0.01190 -0.0582 1.0000 0.1630
-2.250 -0.0188 0.02061 0.01012 -0.0574 1.0000 0.2008
-2.000 0.0096 0.01887 0.00872 -0.0569 1.0000 0.2875
-1.750 0.0334 0.01617 0.00760 -0.0551 1.0000 0.5670
-1.500 0.0505 0.01444 0.00651 -0.0512 1.0000 1.0000
-1.250 0.0776 0.01454 0.00602 -0.0514 1.0000 1.0000
-1.000 0.1033 0.01466 0.00570 -0.0513 1.0000 1.0000
-0.750 0.1285 0.01482 0.00554 -0.0511 1.0000 1.0000
-0.500 0.1533 0.01501 0.00547 -0.0510 1.0000 1.0000
-0.250 0.1779 0.01524 0.00548 -0.0509 1.0000 1.0000
0.000 0.2021 0.01552 0.00558 -0.0509 1.0000 1.0000
0.250 0.2259 0.01584 0.00574 -0.0509 1.0000 1.0000
0.500 0.2492 0.01623 0.00600 -0.0510 1.0000 1.0000
0.750 0.2721 0.01667 0.00637 -0.0512 1.0000 1.0000
1.000 0.2944 0.01720 0.00683 -0.0514 1.0000 1.0000
1.250 0.3161 0.01781 0.00740 -0.0518 1.0000 1.0000
1.500 0.3371 0.01852 0.00809 -0.0523 1.0000 1.0000
1.750 0.3573 0.01935 0.00893 -0.0530 1.0000 1.0000
2.000 0.3787 0.02031 0.00992 -0.0542 0.9988 1.0000
2.250 0.4574 0.02127 0.01103 -0.0653 0.9693 1.0000
2.500 0.5241 0.02184 0.01177 -0.0731 0.9352 1.0000
2.750 0.5930 0.02193 0.01211 -0.0799 0.9014 1.0000
3.000 0.6421 0.02182 0.01227 -0.0820 0.8652 1.0000
3.250 0.6841 0.02148 0.01210 -0.0818 0.8300 1.0000
3.500 0.7125 0.02132 0.01206 -0.0792 0.7910 1.0000
3.750 0.7373 0.02118 0.01205 -0.0758 0.7507 1.0000
4.000 0.7600 0.02110 0.01198 -0.0721 0.7081 1.0000
4.250 0.7818 0.02112 0.01193 -0.0683 0.6628 1.0000
4.500 0.8026 0.02138 0.01211 -0.0649 0.6108 1.0000
4.750 0.8236 0.02180 0.01236 -0.0618 0.5559 1.0000
5.000 0.8446 0.02244 0.01283 -0.0590 0.4988 1.0000
5.250 0.8659 0.02334 0.01347 -0.0566 0.4426 1.0000
5.500 0.8878 0.02449 0.01442 -0.0548 0.3910 1.0000
5.750 0.9103 0.02582 0.01557 -0.0532 0.3469 1.0000
6.000 0.9330 0.02729 0.01695 -0.0519 0.3085 1.0000
6.250 0.9564 0.02897 0.01863 -0.0508 0.2771 1.0000
6.500 0.9794 0.03070 0.02035 -0.0497 0.2485 1.0000
6.750 1.0024 0.03290 0.02275 -0.0487 0.2253 1.0000
7.000 1.0245 0.03497 0.02486 -0.0476 0.2027 1.0000
7.250 1.0458 0.03784 0.02813 -0.0466 0.1856 1.0000
7.500 1.0664 0.04007 0.03041 -0.0455 0.1661 1.0000
7.750 1.0837 0.04398 0.03492 -0.0443 0.1548 1.0000
8.000 1.0996 0.04713 0.03845 -0.0431 0.1405 1.0000
8.250 1.1100 0.05181 0.04368 -0.0419 0.1326 1.0000
8.500 1.1173 0.05685 0.04927 -0.0409 0.1276 1.0000
8.750 1.1221 0.06166 0.05440 -0.0401 0.1212 1.0000
9.000 1.1138 0.06778 0.06106 -0.0399 0.1195 1.0000
9.250 1.1013 0.07416 0.06780 -0.0404 0.1195 1.0000
9.500 1.0859 0.08068 0.07454 -0.0416 0.1208 1.0000
9.750 1.0706 0.08704 0.08101 -0.0431 0.1221 1.0000
10.000 1.0585 0.09324 0.08725 -0.0444 0.1233 1.0000
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Polar data table (+)
Polar graphs
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