AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 200,000 Max Cl/Cd: 71.61 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag26-il-200000.txt Download as CSV file: xf-ag26-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4798 0.09556 0.09215 -0.0007 1.0000 0.0360
-7.750 -0.4753 0.09200 0.08863 -0.0032 1.0000 0.0378
-7.500 -0.4714 0.08833 0.08501 -0.0071 1.0000 0.0394
-7.250 -0.4595 0.08370 0.08042 -0.0181 1.0000 0.0408
-7.000 -0.4410 0.07812 0.07481 -0.0287 1.0000 0.0412
-6.750 -0.4277 0.07097 0.06763 -0.0365 1.0000 0.0417
-6.500 -0.4260 0.06736 0.06410 -0.0326 1.0000 0.0430
-6.250 -0.4137 0.06445 0.06119 -0.0327 1.0000 0.0445
-6.000 -0.3973 0.06059 0.05731 -0.0358 1.0000 0.0465
-5.750 -0.3769 0.05572 0.05236 -0.0410 1.0000 0.0494
-5.500 -0.3454 0.04700 0.04302 -0.0529 1.0000 0.0549
-5.250 -0.3312 0.04381 0.03999 -0.0522 1.0000 0.0566
-5.000 -0.3129 0.04117 0.03732 -0.0524 1.0000 0.0592
-4.750 -0.2855 0.03653 0.03204 -0.0561 1.0000 0.0685
-4.500 -0.2725 0.02100 0.01704 -0.0500 1.0000 0.0704
-4.250 -0.2256 0.02306 0.01702 -0.0571 1.0000 0.0303
-4.000 -0.2004 0.02131 0.01497 -0.0564 1.0000 0.0293
-3.750 -0.1742 0.01904 0.01230 -0.0561 1.0000 0.0296
-3.500 -0.1481 0.01647 0.00947 -0.0564 1.0000 0.0340
-3.250 -0.1213 0.01507 0.00788 -0.0559 1.0000 0.0358
-3.000 -0.0942 0.01391 0.00660 -0.0555 1.0000 0.0390
-2.750 -0.0664 0.01276 0.00544 -0.0556 1.0000 0.0468
-2.500 -0.0382 0.01194 0.00463 -0.0557 1.0000 0.0635
-2.250 -0.0078 0.01092 0.00391 -0.0566 1.0000 0.1331
-2.000 0.0224 0.01005 0.00375 -0.0579 1.0000 0.3059
-1.750 0.0508 0.00959 0.00378 -0.0586 1.0000 0.4494
-1.500 0.0871 0.00905 0.00378 -0.0606 0.9960 0.6058
-1.250 0.1180 0.00817 0.00370 -0.0601 0.9882 0.8755
-1.000 0.1660 0.00807 0.00348 -0.0642 0.9772 1.0000
-0.750 0.2132 0.00806 0.00330 -0.0681 0.9689 1.0000
-0.500 0.2537 0.00802 0.00314 -0.0705 0.9564 1.0000
-0.250 0.2910 0.00797 0.00299 -0.0721 0.9425 1.0000
0.000 0.3243 0.00793 0.00286 -0.0727 0.9268 1.0000
0.250 0.3530 0.00791 0.00277 -0.0723 0.9076 1.0000
0.500 0.3802 0.00791 0.00268 -0.0716 0.8883 1.0000
0.750 0.4060 0.00795 0.00263 -0.0706 0.8673 1.0000
1.000 0.4315 0.00800 0.00258 -0.0695 0.8460 1.0000
1.250 0.4570 0.00808 0.00257 -0.0685 0.8230 1.0000
1.500 0.4826 0.00817 0.00258 -0.0675 0.8000 1.0000
1.750 0.5084 0.00829 0.00259 -0.0666 0.7760 1.0000
2.000 0.5343 0.00843 0.00263 -0.0658 0.7504 1.0000
2.250 0.5603 0.00859 0.00269 -0.0651 0.7241 1.0000
2.500 0.5863 0.00876 0.00276 -0.0644 0.6965 1.0000
2.750 0.6123 0.00896 0.00287 -0.0637 0.6670 1.0000
3.000 0.6382 0.00919 0.00298 -0.0630 0.6357 1.0000
3.250 0.6641 0.00943 0.00311 -0.0624 0.6017 1.0000
3.500 0.6899 0.00971 0.00326 -0.0618 0.5666 1.0000
3.750 0.7156 0.01002 0.00348 -0.0612 0.5291 1.0000
4.000 0.7412 0.01035 0.00369 -0.0607 0.4902 1.0000
4.250 0.7666 0.01074 0.00394 -0.0602 0.4501 1.0000
4.500 0.7919 0.01116 0.00423 -0.0597 0.4099 1.0000
4.750 0.8171 0.01163 0.00459 -0.0592 0.3710 1.0000
5.000 0.8421 0.01214 0.00496 -0.0588 0.3328 1.0000
5.250 0.8672 0.01266 0.00538 -0.0584 0.2960 1.0000
5.500 0.8920 0.01323 0.00584 -0.0580 0.2604 1.0000
5.750 0.9165 0.01385 0.00635 -0.0576 0.2254 1.0000
6.000 0.9408 0.01452 0.00695 -0.0572 0.1919 1.0000
6.250 0.9649 0.01525 0.00759 -0.0567 0.1612 1.0000
6.500 0.9886 0.01605 0.00832 -0.0562 0.1357 1.0000
6.750 1.0117 0.01695 0.00912 -0.0556 0.1138 1.0000
7.000 1.0351 0.01780 0.00999 -0.0551 0.0945 1.0000
7.250 1.0566 0.01896 0.01106 -0.0543 0.0771 1.0000
7.500 1.0792 0.01995 0.01213 -0.0536 0.0616 1.0000
7.750 1.1002 0.02124 0.01352 -0.0526 0.0485 1.0000
8.000 1.1202 0.02269 0.01502 -0.0516 0.0382 1.0000
8.250 1.1391 0.02438 0.01677 -0.0504 0.0315 1.0000
8.500 1.1579 0.02633 0.01892 -0.0491 0.0269 1.0000
8.750 1.1773 0.02777 0.02048 -0.0481 0.0232 1.0000
9.000 1.1904 0.03148 0.02440 -0.0464 0.0211 1.0000
9.250 1.2050 0.03471 0.02802 -0.0447 0.0202 1.0000
9.500 1.2180 0.03776 0.03149 -0.0430 0.0196 1.0000
9.750 1.2268 0.04119 0.03536 -0.0411 0.0190 1.0000
10.000 1.2326 0.04435 0.03893 -0.0392 0.0181 1.0000
10.250 1.2356 0.04728 0.04220 -0.0374 0.0171 1.0000
10.500 1.2343 0.05035 0.04560 -0.0356 0.0164 1.0000
10.750 1.2243 0.05378 0.04931 -0.0333 0.0161 1.0000
11.000 1.2065 0.05789 0.05372 -0.0317 0.0162 1.0000
11.250 1.1854 0.06297 0.05908 -0.0320 0.0164 1.0000
11.500 1.1636 0.06902 0.06537 -0.0346 0.0165 1.0000
11.750 1.1387 0.07682 0.07337 -0.0396 0.0170 1.0000
12.000 1.1100 0.08686 0.08362 -0.0470 0.0179 1.0000
12.250 1.0821 0.09801 0.09490 -0.0550 0.0190 1.0000
12.500 1.0543 0.10952 0.10645 -0.0621 0.0202 1.0000
13.250 0.9731 0.15528 0.15216 -0.0857 0.0278 1.0000
13.500 0.9707 0.16082 0.15768 -0.0874 0.0294 1.0000
13.750 0.7769 0.14540 0.14242 -0.0616 0.0284 1.0000
14.000 0.7684 0.15007 0.14708 -0.0632 0.0290 1.0000
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