AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 100,000 Max Cl/Cd: 54.47 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag26-il-100000.txt Download as CSV file: xf-ag26-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4820 0.10313 0.09833 0.0008 1.0000 0.0752
-8.000 -0.4803 0.10009 0.09534 -0.0025 1.0000 0.0783
-7.750 -0.4852 0.09782 0.09318 -0.0112 1.0000 0.0801
-7.500 -0.4793 0.09285 0.08828 -0.0161 1.0000 0.0812
-7.250 -0.4665 0.08897 0.08439 -0.0087 1.0000 0.0840
-7.000 -0.4569 0.08552 0.08097 -0.0102 1.0000 0.0878
-6.750 -0.4424 0.08052 0.07591 -0.0313 1.0000 0.0939
-6.500 -0.4357 0.07621 0.07172 -0.0252 1.0000 0.0958
-6.250 -0.4240 0.07320 0.06874 -0.0229 1.0000 0.0997
-6.000 -0.4032 0.06712 0.06252 -0.0373 1.0000 0.1086
-5.750 -0.3929 0.06429 0.05980 -0.0328 1.0000 0.1117
-5.500 -0.3713 0.05919 0.05454 -0.0412 1.0000 0.1229
-5.250 -0.3582 0.05664 0.05207 -0.0385 1.0000 0.1294
-5.000 -0.3401 0.05307 0.04846 -0.0409 1.0000 0.1433
-4.750 -0.3187 0.04919 0.04441 -0.0452 1.0000 0.1646
-4.500 -0.3009 0.04614 0.04132 -0.0452 1.0000 0.1794
-4.250 -0.2380 0.03062 0.02394 -0.0576 1.0000 0.0699
-4.000 -0.2095 0.02685 0.01962 -0.0578 1.0000 0.0624
-3.750 -0.1808 0.02358 0.01570 -0.0579 1.0000 0.0596
-3.500 -0.1529 0.02122 0.01288 -0.0575 1.0000 0.0601
-3.250 -0.1258 0.01999 0.01122 -0.0568 1.0000 0.0669
-3.000 -0.0992 0.01800 0.00922 -0.0565 1.0000 0.0742
-2.750 -0.0724 0.01663 0.00783 -0.0561 1.0000 0.0883
-2.500 -0.0449 0.01530 0.00661 -0.0559 1.0000 0.1175
-2.250 -0.0156 0.01361 0.00557 -0.0566 1.0000 0.2332
-2.000 0.0109 0.01226 0.00537 -0.0567 1.0000 0.4934
-1.750 0.0317 0.01138 0.00526 -0.0545 1.0000 0.7082
-1.500 0.0473 0.01079 0.00500 -0.0513 1.0000 1.0000
-1.250 0.0740 0.01095 0.00484 -0.0516 1.0000 1.0000
-1.000 0.1000 0.01114 0.00476 -0.0518 1.0000 1.0000
-0.750 0.1254 0.01138 0.00480 -0.0520 1.0000 1.0000
-0.500 0.1503 0.01167 0.00492 -0.0523 1.0000 1.0000
-0.250 0.1747 0.01201 0.00512 -0.0526 1.0000 1.0000
0.000 0.2035 0.01239 0.00537 -0.0538 0.9977 1.0000
0.250 0.2591 0.01268 0.00554 -0.0598 0.9839 1.0000
0.500 0.3137 0.01286 0.00565 -0.0654 0.9693 1.0000
0.750 0.3647 0.01294 0.00569 -0.0700 0.9529 1.0000
1.000 0.4115 0.01294 0.00568 -0.0735 0.9353 1.0000
1.250 0.4544 0.01287 0.00561 -0.0758 0.9171 1.0000
1.500 0.4911 0.01279 0.00556 -0.0767 0.8973 1.0000
1.750 0.5219 0.01273 0.00550 -0.0762 0.8750 1.0000
2.000 0.5492 0.01271 0.00547 -0.0751 0.8511 1.0000
2.250 0.5750 0.01271 0.00544 -0.0735 0.8266 1.0000
2.500 0.5996 0.01274 0.00548 -0.0718 0.8007 1.0000
2.750 0.6238 0.01282 0.00551 -0.0700 0.7728 1.0000
3.000 0.6479 0.01293 0.00558 -0.0684 0.7429 1.0000
3.250 0.6721 0.01308 0.00567 -0.0667 0.7111 1.0000
3.500 0.6963 0.01327 0.00575 -0.0652 0.6781 1.0000
3.750 0.7204 0.01350 0.00596 -0.0637 0.6407 1.0000
4.000 0.7445 0.01379 0.00615 -0.0624 0.6016 1.0000
4.250 0.7686 0.01414 0.00638 -0.0611 0.5606 1.0000
4.500 0.7925 0.01455 0.00666 -0.0599 0.5179 1.0000
4.750 0.8163 0.01503 0.00700 -0.0588 0.4745 1.0000
5.000 0.8399 0.01560 0.00745 -0.0578 0.4310 1.0000
5.250 0.8632 0.01626 0.00795 -0.0569 0.3882 1.0000
5.500 0.8864 0.01700 0.00854 -0.0560 0.3454 1.0000
5.750 0.9093 0.01783 0.00922 -0.0551 0.3038 1.0000
6.000 0.9318 0.01878 0.01001 -0.0543 0.2646 1.0000
6.250 0.9543 0.01979 0.01098 -0.0535 0.2272 1.0000
6.500 0.9764 0.02096 0.01198 -0.0527 0.1963 1.0000
6.750 0.9985 0.02217 0.01310 -0.0518 0.1684 1.0000
7.000 1.0207 0.02343 0.01438 -0.0510 0.1441 1.0000
7.250 1.0423 0.02482 0.01583 -0.0501 0.1216 1.0000
7.500 1.0635 0.02660 0.01748 -0.0492 0.1033 1.0000
7.750 1.0841 0.02839 0.01945 -0.0481 0.0859 1.0000
8.000 1.1046 0.03058 0.02185 -0.0469 0.0725 1.0000
8.250 1.1243 0.03310 0.02449 -0.0459 0.0622 1.0000
8.500 1.1436 0.03540 0.02702 -0.0446 0.0544 1.0000
8.750 1.1593 0.03872 0.03079 -0.0432 0.0486 1.0000
9.000 1.1737 0.04233 0.03490 -0.0415 0.0456 1.0000
9.250 1.1854 0.04606 0.03902 -0.0400 0.0436 1.0000
9.500 1.1930 0.05048 0.04364 -0.0388 0.0415 1.0000
9.750 1.1896 0.05578 0.04946 -0.0371 0.0405 1.0000
10.000 1.1831 0.05978 0.05401 -0.0352 0.0397 1.0000
10.250 1.1714 0.06428 0.05892 -0.0336 0.0394 1.0000
10.500 1.1547 0.06871 0.06363 -0.0322 0.0395 1.0000
10.750 1.1353 0.07328 0.06841 -0.0318 0.0397 1.0000
11.000 1.1153 0.07857 0.07387 -0.0331 0.0401 1.0000
11.250 1.0967 0.08471 0.08012 -0.0356 0.0405 1.0000
11.500 0.9231 0.09019 0.08610 -0.0326 0.0499 1.0000
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Polar data table (+)
Polar graphs
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