AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 100,000 Max Cl/Cd: 53.17 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag26-il-100000-n5.txt Download as CSV file: xf-ag26-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3874 0.09233 0.08773 -0.0104 1.0000 0.0441
-8.250 -0.3870 0.08828 0.08371 -0.0119 1.0000 0.0438
-8.000 -0.3888 0.08219 0.07761 -0.0149 1.0000 0.0286
-7.750 -0.3848 0.07830 0.07376 -0.0147 1.0000 0.0272
-7.500 -0.3840 0.07423 0.06972 -0.0158 1.0000 0.0263
-7.250 -0.4645 0.08284 0.07813 -0.0128 1.0000 0.0270
-7.000 -0.4559 0.07843 0.07375 -0.0165 1.0000 0.0257
-6.750 -0.4451 0.07338 0.06873 -0.0217 1.0000 0.0244
-6.500 -0.4314 0.06745 0.06280 -0.0283 1.0000 0.0231
-6.250 -0.4130 0.05930 0.05456 -0.0376 1.0000 0.0215
-5.750 -0.3669 0.04429 0.03888 -0.0502 1.0000 0.0194
-5.500 -0.3457 0.03910 0.03330 -0.0532 1.0000 0.0192
-5.250 -0.3222 0.03449 0.02818 -0.0553 1.0000 0.0193
-5.000 -0.2992 0.03035 0.02358 -0.0569 1.0000 0.0206
-4.750 -0.2761 0.02850 0.02155 -0.0573 1.0000 0.0229
-4.500 -0.2505 0.02584 0.01842 -0.0576 1.0000 0.0243
-4.250 -0.2239 0.02323 0.01529 -0.0576 1.0000 0.0250
-4.000 -0.1975 0.02113 0.01279 -0.0573 1.0000 0.0262
-3.750 -0.1713 0.01945 0.01079 -0.0568 1.0000 0.0279
-3.500 -0.1458 0.01806 0.00921 -0.0564 1.0000 0.0317
-3.250 -0.1204 0.01712 0.00821 -0.0561 1.0000 0.0373
-3.000 -0.0941 0.01605 0.00702 -0.0558 1.0000 0.0429
-2.750 -0.0681 0.01529 0.00626 -0.0556 1.0000 0.0574
-2.500 -0.0414 0.01452 0.00558 -0.0557 1.0000 0.0852
-2.250 -0.0145 0.01376 0.00507 -0.0559 1.0000 0.1509
-2.000 0.0118 0.01312 0.00487 -0.0562 1.0000 0.2621
-1.750 0.0500 0.01253 0.00474 -0.0587 0.9920 0.4078
-1.500 0.0882 0.01202 0.00462 -0.0609 0.9833 0.5449
-1.250 0.1217 0.01143 0.00449 -0.0616 0.9732 0.6995
-1.000 0.1572 0.01082 0.00423 -0.0621 0.9599 1.0000
-0.750 0.1952 0.01085 0.00405 -0.0641 0.9466 1.0000
-0.500 0.2319 0.01088 0.00390 -0.0657 0.9321 1.0000
-0.250 0.2672 0.01091 0.00376 -0.0670 0.9164 1.0000
0.000 0.3010 0.01093 0.00365 -0.0678 0.8995 1.0000
0.250 0.3315 0.01097 0.00358 -0.0680 0.8796 1.0000
0.500 0.3616 0.01101 0.00351 -0.0680 0.8599 1.0000
0.750 0.3899 0.01107 0.00347 -0.0676 0.8383 1.0000
1.000 0.4179 0.01114 0.00343 -0.0671 0.8168 1.0000
1.250 0.4449 0.01124 0.00344 -0.0665 0.7932 1.0000
1.500 0.4717 0.01135 0.00348 -0.0658 0.7691 1.0000
1.750 0.4984 0.01148 0.00352 -0.0651 0.7444 1.0000
2.000 0.5248 0.01163 0.00357 -0.0644 0.7188 1.0000
2.250 0.5510 0.01181 0.00366 -0.0636 0.6921 1.0000
2.500 0.5772 0.01201 0.00377 -0.0629 0.6642 1.0000
2.750 0.6032 0.01223 0.00394 -0.0622 0.6350 1.0000
3.000 0.6291 0.01247 0.00410 -0.0615 0.6044 1.0000
3.250 0.6549 0.01275 0.00429 -0.0609 0.5725 1.0000
3.500 0.6804 0.01306 0.00449 -0.0602 0.5389 1.0000
3.750 0.7058 0.01340 0.00479 -0.0595 0.5028 1.0000
4.000 0.7311 0.01379 0.00506 -0.0589 0.4655 1.0000
4.250 0.7561 0.01422 0.00538 -0.0583 0.4279 1.0000
4.500 0.7810 0.01469 0.00574 -0.0577 0.3907 1.0000
4.750 0.8058 0.01519 0.00615 -0.0572 0.3545 1.0000
5.000 0.8304 0.01574 0.00666 -0.0567 0.3202 1.0000
5.250 0.8550 0.01631 0.00717 -0.0562 0.2872 1.0000
5.500 0.8794 0.01693 0.00774 -0.0557 0.2554 1.0000
5.750 0.9036 0.01759 0.00835 -0.0552 0.2254 1.0000
6.000 0.9274 0.01830 0.00902 -0.0547 0.1966 1.0000
6.250 0.9511 0.01906 0.00981 -0.0542 0.1700 1.0000
6.500 0.9745 0.01987 0.01061 -0.0537 0.1453 1.0000
6.750 0.9974 0.02075 0.01151 -0.0531 0.1245 1.0000
7.000 1.0198 0.02171 0.01248 -0.0525 0.1052 1.0000
7.250 1.0414 0.02280 0.01356 -0.0518 0.0895 1.0000
7.500 1.0631 0.02389 0.01474 -0.0511 0.0741 1.0000
7.750 1.0837 0.02513 0.01614 -0.0503 0.0612 1.0000
8.000 1.1033 0.02651 0.01760 -0.0494 0.0501 1.0000
8.250 1.1215 0.02805 0.01922 -0.0484 0.0410 1.0000
8.500 1.1404 0.02959 0.02099 -0.0473 0.0340 1.0000
8.750 1.1550 0.03168 0.02317 -0.0460 0.0296 1.0000
9.000 1.1725 0.03338 0.02518 -0.0448 0.0250 1.0000
9.250 1.1866 0.03538 0.02735 -0.0435 0.0224 1.0000
9.500 1.1957 0.03845 0.03057 -0.0418 0.0207 1.0000
9.750 1.2075 0.04118 0.03371 -0.0402 0.0195 1.0000
10.000 1.2160 0.04396 0.03691 -0.0386 0.0179 1.0000
10.500 1.2232 0.04926 0.04286 -0.0356 0.0153 1.0000
10.750 1.2189 0.05217 0.04603 -0.0338 0.0148 1.0000
11.000 1.2102 0.05561 0.04972 -0.0324 0.0145 1.0000
11.250 1.1987 0.05961 0.05397 -0.0321 0.0143 1.0000
11.500 1.1849 0.06433 0.05894 -0.0330 0.0142 1.0000
11.750 1.1690 0.06995 0.06481 -0.0355 0.0142 1.0000
12.000 1.1508 0.07675 0.07187 -0.0395 0.0143 1.0000
12.250 1.1289 0.08523 0.08061 -0.0452 0.0145 1.0000
12.500 1.0995 0.09669 0.09232 -0.0534 0.0151 1.0000
12.750 1.0515 0.11485 0.11060 -0.0650 0.0174 1.0000
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Polar data table (+)
Polar graphs
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