AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG26 Bubble Dancer DLG by Mark Drela (ag26-il) Reynolds number: 50,000 Max Cl/Cd: 36.82 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag26-il-50000.txt Download as CSV file: xf-ag26-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5140 0.12243 0.11571 0.0055 1.0000 0.1624
-8.750 -0.4930 0.11619 0.10940 0.0076 1.0000 0.1722
-8.500 -0.5056 0.11580 0.10913 0.0034 1.0000 0.1763
-8.250 -0.4838 0.10965 0.10296 0.0057 1.0000 0.1863
-8.000 -0.4898 0.10763 0.10107 0.0028 1.0000 0.1914
-7.750 -0.4773 0.10355 0.09700 0.0034 1.0000 0.2018
-7.500 -0.4698 0.09969 0.09320 0.0031 1.0000 0.2091
-7.250 -0.4804 0.09882 0.09248 -0.0017 1.0000 0.2179
-7.000 -0.4630 0.09382 0.08748 0.0012 1.0000 0.2293
-6.750 -0.4539 0.09006 0.08378 0.0010 1.0000 0.2398
-6.500 -0.4471 0.08670 0.08049 -0.0001 1.0000 0.2519
-6.250 -0.4394 0.08337 0.07722 -0.0010 1.0000 0.2657
-6.000 -0.4309 0.08008 0.07399 -0.0018 1.0000 0.2817
-5.750 -0.4269 0.07743 0.07143 -0.0058 1.0000 0.3020
-5.500 -0.4134 0.07350 0.06754 -0.0027 1.0000 0.3195
-5.250 -0.4046 0.07044 0.06455 -0.0020 1.0000 0.3465
-5.000 -0.3943 0.06736 0.06149 0.0007 1.0000 0.3770
-4.500 -0.2825 0.04356 0.03586 -0.0537 1.0000 0.1351
-4.250 -0.2589 0.03941 0.03164 -0.0542 1.0000 0.1305
-4.000 -0.2249 0.03445 0.02576 -0.0570 1.0000 0.1194
-3.750 -0.1958 0.03090 0.02170 -0.0578 1.0000 0.1174
-3.500 -0.1652 0.02806 0.01810 -0.0582 1.0000 0.1211
-3.250 -0.1385 0.02584 0.01567 -0.0579 1.0000 0.1339
-3.000 -0.1108 0.02361 0.01323 -0.0574 1.0000 0.1460
-2.750 -0.0843 0.02189 0.01145 -0.0569 1.0000 0.1778
-2.500 -0.0577 0.02012 0.00990 -0.0561 1.0000 0.2348
-2.250 -0.0300 0.01794 0.00862 -0.0554 1.0000 0.4065
-2.000 -0.0192 0.01569 0.00800 -0.0498 1.0000 0.7072
-1.750 0.0034 0.01471 0.00698 -0.0478 1.0000 1.0000
-1.500 0.0313 0.01479 0.00648 -0.0483 1.0000 1.0000
-1.250 0.0574 0.01492 0.00618 -0.0485 1.0000 1.0000
-1.000 0.0830 0.01508 0.00597 -0.0486 1.0000 1.0000
-0.750 0.1082 0.01527 0.00588 -0.0487 1.0000 1.0000
-0.500 0.1329 0.01551 0.00588 -0.0488 1.0000 1.0000
-0.250 0.1572 0.01579 0.00597 -0.0489 1.0000 1.0000
0.000 0.1811 0.01612 0.00614 -0.0490 1.0000 1.0000
0.250 0.2045 0.01651 0.00637 -0.0492 1.0000 1.0000
0.500 0.2274 0.01696 0.00671 -0.0494 1.0000 1.0000
0.750 0.2499 0.01748 0.00715 -0.0498 1.0000 1.0000
1.000 0.2718 0.01807 0.00769 -0.0502 1.0000 1.0000
1.250 0.2930 0.01876 0.00833 -0.0507 1.0000 1.0000
1.500 0.3136 0.01955 0.00910 -0.0513 1.0000 1.0000
1.750 0.3334 0.02045 0.01001 -0.0521 1.0000 1.0000
2.000 0.3976 0.02148 0.01110 -0.0607 0.9768 1.0000
2.250 0.4650 0.02222 0.01199 -0.0691 0.9477 1.0000
2.500 0.5287 0.02264 0.01258 -0.0759 0.9174 1.0000
2.750 0.5896 0.02270 0.01285 -0.0810 0.8873 1.0000
3.000 0.6349 0.02264 0.01304 -0.0825 0.8554 1.0000
3.250 0.6720 0.02252 0.01308 -0.0821 0.8224 1.0000
3.500 0.7053 0.02226 0.01294 -0.0804 0.7900 1.0000
3.750 0.7308 0.02223 0.01307 -0.0776 0.7537 1.0000
4.000 0.7559 0.02214 0.01302 -0.0745 0.7175 1.0000
4.250 0.7793 0.02213 0.01301 -0.0712 0.6790 1.0000
4.500 0.8017 0.02228 0.01313 -0.0680 0.6376 1.0000
4.750 0.8237 0.02257 0.01336 -0.0651 0.5938 1.0000
5.000 0.8456 0.02302 0.01380 -0.0625 0.5479 1.0000
5.250 0.8678 0.02357 0.01423 -0.0600 0.5021 1.0000
5.500 0.8899 0.02429 0.01476 -0.0578 0.4563 1.0000
5.750 0.9115 0.02526 0.01564 -0.0559 0.4092 1.0000
6.000 0.9333 0.02640 0.01664 -0.0541 0.3649 1.0000
6.250 0.9552 0.02779 0.01798 -0.0525 0.3236 1.0000
6.500 0.9768 0.02933 0.01945 -0.0511 0.2857 1.0000
6.750 0.9990 0.03108 0.02114 -0.0498 0.2532 1.0000
7.000 1.0210 0.03297 0.02296 -0.0485 0.2239 1.0000
7.250 1.0419 0.03508 0.02518 -0.0473 0.1974 1.0000
7.500 1.0617 0.03777 0.02820 -0.0459 0.1753 1.0000
7.750 1.0820 0.04025 0.03063 -0.0448 0.1547 1.0000
8.000 1.0985 0.04367 0.03451 -0.0433 0.1396 1.0000
8.250 1.1143 0.04730 0.03853 -0.0420 0.1271 1.0000
8.500 1.1286 0.05073 0.04216 -0.0408 0.1149 1.0000
8.750 1.1306 0.05632 0.04862 -0.0392 0.1122 1.0000
9.000 1.1283 0.06210 0.05500 -0.0382 0.1105 1.0000
9.250 1.1200 0.06799 0.06137 -0.0377 0.1096 1.0000
9.500 1.1049 0.07423 0.06797 -0.0379 0.1105 1.0000
9.750 1.0867 0.08054 0.07449 -0.0387 0.1122 1.0000
10.000 1.0686 0.08651 0.08056 -0.0398 0.1137 1.0000
10.250 1.0535 0.09273 0.08682 -0.0416 0.1148 1.0000
10.500 1.0420 0.09936 0.09350 -0.0440 0.1157 1.0000
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Polar data table (+)
Polar graphs
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