AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 100,000 Max Cl/Cd: 53.09 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag25-il-100000-n5.txt Download as CSV file: xf-ag25-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG25 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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4832 0.09377 0.08895 -0.0087 1.0000 0.0271
-8.000 -0.4796 0.08985 0.08508 -0.0104 1.0000 0.0260
-7.750 -0.4771 0.08572 0.08101 -0.0127 1.0000 0.0250
-7.500 -0.4747 0.08127 0.07661 -0.0160 1.0000 0.0241
-7.250 -0.4690 0.07585 0.07125 -0.0215 1.0000 0.0231
-7.000 -0.4605 0.06893 0.06434 -0.0294 1.0000 0.0219
-6.500 -0.4299 0.05093 0.04585 -0.0472 1.0000 0.0194
-6.250 -0.4158 0.04546 0.04011 -0.0506 1.0000 0.0192
-6.000 -0.3988 0.04035 0.03460 -0.0531 1.0000 0.0191
-5.750 -0.3792 0.03581 0.02957 -0.0548 1.0000 0.0191
-5.500 -0.3573 0.03197 0.02517 -0.0558 1.0000 0.0196
-5.250 -0.3365 0.02887 0.02174 -0.0565 1.0000 0.0214
-5.000 -0.3135 0.02702 0.01962 -0.0566 1.0000 0.0235
-4.750 -0.2885 0.02458 0.01671 -0.0564 1.0000 0.0247
-4.500 -0.2631 0.02241 0.01413 -0.0560 1.0000 0.0257
-4.250 -0.2376 0.02063 0.01205 -0.0555 1.0000 0.0272
-4.000 -0.2123 0.01935 0.01051 -0.0549 1.0000 0.0293
-3.750 -0.1877 0.01809 0.00926 -0.0547 1.0000 0.0350
-3.500 -0.1621 0.01709 0.00806 -0.0543 1.0000 0.0399
-3.250 -0.1362 0.01616 0.00711 -0.0542 1.0000 0.0495
-3.000 -0.1096 0.01534 0.00627 -0.0542 1.0000 0.0678
-2.750 -0.0825 0.01446 0.00566 -0.0546 1.0000 0.1198
-2.500 -0.0556 0.01370 0.00535 -0.0551 1.0000 0.2230
-2.250 -0.0210 0.01311 0.00516 -0.0570 0.9951 0.3485
-2.000 0.0167 0.01266 0.00503 -0.0592 0.9867 0.4611
-1.750 0.0543 0.01229 0.00492 -0.0611 0.9783 0.5639
-1.500 0.0906 0.01191 0.00483 -0.0625 0.9696 0.6684
-1.250 0.1204 0.01152 0.00470 -0.0620 0.9582 0.7849
-1.000 0.1572 0.01110 0.00441 -0.0629 0.9452 1.0000
-0.750 0.1936 0.01112 0.00424 -0.0646 0.9321 1.0000
-0.500 0.2285 0.01113 0.00408 -0.0659 0.9180 1.0000
-0.250 0.2621 0.01115 0.00396 -0.0668 0.9028 1.0000
0.000 0.2944 0.01116 0.00385 -0.0674 0.8869 1.0000
0.250 0.3246 0.01119 0.00377 -0.0675 0.8690 1.0000
0.500 0.3539 0.01123 0.00371 -0.0674 0.8501 1.0000
0.750 0.3829 0.01127 0.00365 -0.0672 0.8311 1.0000
1.000 0.4105 0.01134 0.00364 -0.0667 0.8098 1.0000
1.250 0.4381 0.01141 0.00362 -0.0662 0.7885 1.0000
1.500 0.4651 0.01151 0.00365 -0.0656 0.7651 1.0000
1.750 0.4919 0.01163 0.00369 -0.0650 0.7410 1.0000
2.000 0.5185 0.01177 0.00374 -0.0644 0.7160 1.0000
2.250 0.5450 0.01194 0.00381 -0.0637 0.6898 1.0000
2.500 0.5713 0.01213 0.00395 -0.0631 0.6624 1.0000
2.750 0.5975 0.01234 0.00408 -0.0624 0.6339 1.0000
3.000 0.6236 0.01259 0.00423 -0.0618 0.6045 1.0000
3.250 0.6495 0.01286 0.00442 -0.0612 0.5744 1.0000
3.500 0.6753 0.01316 0.00463 -0.0606 0.5439 1.0000
3.750 0.7010 0.01349 0.00492 -0.0600 0.5132 1.0000
4.000 0.7265 0.01385 0.00520 -0.0595 0.4820 1.0000
4.250 0.7520 0.01423 0.00553 -0.0590 0.4506 1.0000
4.500 0.7772 0.01465 0.00588 -0.0584 0.4194 1.0000
4.750 0.8022 0.01511 0.00631 -0.0579 0.3884 1.0000
5.000 0.8272 0.01559 0.00675 -0.0574 0.3573 1.0000
5.250 0.8520 0.01610 0.00723 -0.0569 0.3263 1.0000
5.500 0.8764 0.01666 0.00775 -0.0564 0.2954 1.0000
5.750 0.9006 0.01726 0.00831 -0.0559 0.2651 1.0000
6.000 0.9246 0.01791 0.00897 -0.0554 0.2354 1.0000
6.250 0.9483 0.01860 0.00965 -0.0549 0.2054 1.0000
6.500 0.9716 0.01936 0.01040 -0.0544 0.1765 1.0000
6.750 0.9944 0.02020 0.01122 -0.0538 0.1486 1.0000
7.000 1.0167 0.02114 0.01213 -0.0532 0.1216 1.0000
7.250 1.0382 0.02220 0.01316 -0.0526 0.0971 1.0000
7.500 1.0586 0.02344 0.01439 -0.0518 0.0758 1.0000
7.750 1.0787 0.02473 0.01573 -0.0509 0.0575 1.0000
8.000 1.0971 0.02625 0.01732 -0.0499 0.0452 1.0000
8.250 1.1145 0.02789 0.01905 -0.0487 0.0361 1.0000
8.500 1.1297 0.02976 0.02102 -0.0474 0.0306 1.0000
8.750 1.1462 0.03149 0.02299 -0.0460 0.0258 1.0000
9.000 1.1610 0.03332 0.02498 -0.0447 0.0227 1.0000
9.250 1.1713 0.03589 0.02768 -0.0430 0.0208 1.0000
9.500 1.1836 0.03846 0.03053 -0.0414 0.0195 1.0000
9.750 1.1954 0.04084 0.03326 -0.0398 0.0178 1.0000
10.000 1.2044 0.04316 0.03595 -0.0383 0.0162 1.0000
10.250 1.2102 0.04554 0.03857 -0.0368 0.0150 1.0000
10.500 1.2113 0.04831 0.04158 -0.0349 0.0145 1.0000
10.750 1.2075 0.05133 0.04485 -0.0330 0.0141 1.0000
11.000 1.2001 0.05475 0.04852 -0.0315 0.0138 1.0000
11.250 1.1900 0.05865 0.05267 -0.0309 0.0137 1.0000
11.500 1.1774 0.06313 0.05740 -0.0313 0.0136 1.0000
11.750 1.1633 0.06823 0.06276 -0.0328 0.0135 1.0000
12.000 1.1478 0.07406 0.06883 -0.0356 0.0135 1.0000
12.250 1.1312 0.08072 0.07572 -0.0396 0.0136 1.0000
12.500 1.1128 0.08848 0.08372 -0.0447 0.0137 1.0000
12.750 1.0903 0.09806 0.09353 -0.0514 0.0140 1.0000
13.000 1.0569 0.11171 0.10742 -0.0607 0.0146 1.0000
13.250 1.0086 0.13159 0.12733 -0.0722 0.0166 1.0000
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Polar data table (+)
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