AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.01 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag25-il-1000000-n5.txt Download as CSV file: xf-ag25-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5376 0.08305 0.08154 -0.0057 1.0000 0.0028
-8.250 -0.5381 0.07802 0.07653 -0.0094 1.0000 0.0029
-7.750 -0.5663 0.02275 0.01985 -0.0600 1.0000 0.0032
-7.500 -0.5453 0.01991 0.01664 -0.0603 1.0000 0.0034
-7.250 -0.5202 0.01775 0.01417 -0.0609 0.9990 0.0035
-7.000 -0.4889 0.01592 0.01204 -0.0625 0.9962 0.0036
-6.750 -0.4572 0.01445 0.01029 -0.0639 0.9934 0.0037
-6.500 -0.4266 0.01326 0.00890 -0.0648 0.9887 0.0039
-6.250 -0.3947 0.01249 0.00799 -0.0660 0.9841 0.0041
-6.000 -0.3638 0.01179 0.00717 -0.0668 0.9784 0.0043
-5.750 -0.3332 0.01117 0.00644 -0.0675 0.9711 0.0044
-5.500 -0.3039 0.01050 0.00565 -0.0678 0.9622 0.0045
-5.250 -0.2755 0.00992 0.00495 -0.0679 0.9517 0.0046
-5.000 -0.2482 0.00911 0.00395 -0.0678 0.9393 0.0049
-4.750 -0.2213 0.00866 0.00341 -0.0675 0.9254 0.0055
-4.500 -0.1945 0.00839 0.00307 -0.0671 0.9104 0.0061
-4.250 -0.1675 0.00816 0.00275 -0.0668 0.8942 0.0068
-4.000 -0.1403 0.00798 0.00247 -0.0665 0.8774 0.0075
-3.750 -0.1129 0.00776 0.00213 -0.0662 0.8604 0.0087
-3.500 -0.0854 0.00759 0.00190 -0.0661 0.8433 0.0108
-3.250 -0.0576 0.00746 0.00170 -0.0659 0.8255 0.0142
-3.000 -0.0299 0.00734 0.00152 -0.0658 0.8067 0.0194
-2.750 -0.0020 0.00722 0.00136 -0.0657 0.7882 0.0290
-2.500 0.0259 0.00706 0.00120 -0.0657 0.7694 0.0490
-2.250 0.0538 0.00693 0.00108 -0.0657 0.7497 0.0744
-2.000 0.0818 0.00678 0.00097 -0.0657 0.7299 0.1097
-1.750 0.1099 0.00663 0.00088 -0.0658 0.7095 0.1525
-1.500 0.1379 0.00650 0.00080 -0.0658 0.6888 0.2011
-1.250 0.1659 0.00639 0.00075 -0.0659 0.6668 0.2486
-0.750 0.2220 0.00628 0.00069 -0.0660 0.6217 0.3309
-0.500 0.2500 0.00624 0.00068 -0.0661 0.5979 0.3741
-0.250 0.2781 0.00624 0.00068 -0.0661 0.5742 0.4131
0.000 0.3061 0.00623 0.00070 -0.0662 0.5510 0.4534
0.250 0.3340 0.00624 0.00073 -0.0662 0.5263 0.4951
0.500 0.3619 0.00625 0.00076 -0.0662 0.5017 0.5408
0.750 0.3898 0.00625 0.00081 -0.0663 0.4786 0.5893
1.000 0.4175 0.00625 0.00087 -0.0663 0.4552 0.6418
1.250 0.4451 0.00625 0.00094 -0.0662 0.4312 0.6991
1.500 0.4723 0.00623 0.00103 -0.0661 0.4092 0.7647
1.750 0.4982 0.00619 0.00112 -0.0656 0.3874 0.8389
2.000 0.5202 0.00604 0.00117 -0.0640 0.3672 0.9524
2.250 0.5500 0.00619 0.00123 -0.0645 0.3451 1.0000
2.500 0.5778 0.00638 0.00134 -0.0645 0.3232 1.0000
2.750 0.6056 0.00657 0.00144 -0.0645 0.3020 1.0000
3.000 0.6332 0.00678 0.00155 -0.0644 0.2808 1.0000
3.250 0.6608 0.00699 0.00168 -0.0644 0.2604 1.0000
3.500 0.6883 0.00722 0.00183 -0.0644 0.2384 1.0000
3.750 0.7157 0.00745 0.00198 -0.0644 0.2192 1.0000
4.000 0.7430 0.00770 0.00214 -0.0643 0.1983 1.0000
4.250 0.7703 0.00795 0.00232 -0.0643 0.1793 1.0000
4.500 0.7974 0.00822 0.00253 -0.0642 0.1602 1.0000
4.750 0.8243 0.00853 0.00274 -0.0641 0.1402 1.0000
5.000 0.8513 0.00880 0.00296 -0.0640 0.1243 1.0000
5.250 0.8780 0.00912 0.00321 -0.0639 0.1063 1.0000
5.500 0.9044 0.00950 0.00349 -0.0637 0.0868 1.0000
5.750 0.9309 0.00985 0.00379 -0.0636 0.0713 1.0000
6.000 0.9569 0.01026 0.00412 -0.0634 0.0547 1.0000
6.250 0.9828 0.01069 0.00448 -0.0632 0.0403 1.0000
6.500 1.0087 0.01112 0.00485 -0.0630 0.0290 1.0000
6.750 1.0344 0.01155 0.00524 -0.0627 0.0205 1.0000
7.000 1.0602 0.01196 0.00564 -0.0625 0.0154 1.0000
7.250 1.0859 0.01237 0.00607 -0.0622 0.0114 1.0000
7.500 1.1111 0.01285 0.00655 -0.0619 0.0079 1.0000
7.750 1.1364 0.01329 0.00701 -0.0616 0.0061 1.0000
8.000 1.1613 0.01380 0.00754 -0.0612 0.0046 1.0000
8.250 1.1863 0.01426 0.00805 -0.0609 0.0039 1.0000
8.500 1.2108 0.01477 0.00861 -0.0605 0.0034 1.0000
8.750 1.2347 0.01538 0.00927 -0.0600 0.0029 1.0000
9.000 1.2582 0.01606 0.01005 -0.0594 0.0026 1.0000
9.250 1.2819 0.01662 0.01069 -0.0590 0.0024 1.0000
9.500 1.3052 0.01724 0.01139 -0.0584 0.0023 1.0000
9.750 1.3280 0.01791 0.01213 -0.0578 0.0021 1.0000
10.000 1.3502 0.01861 0.01292 -0.0572 0.0020 1.0000
10.250 1.3720 0.01935 0.01375 -0.0565 0.0019 1.0000
10.500 1.3931 0.02014 0.01462 -0.0557 0.0017 1.0000
10.750 1.4134 0.02099 0.01556 -0.0549 0.0016 1.0000
11.000 1.4325 0.02196 0.01664 -0.0540 0.0015 1.0000
11.250 1.4492 0.02317 0.01801 -0.0527 0.0014 1.0000
11.500 1.4615 0.02485 0.01987 -0.0510 0.0013 1.0000
11.750 1.4705 0.02673 0.02196 -0.0490 0.0012 1.0000
12.000 1.4827 0.02808 0.02345 -0.0475 0.0012 1.0000
12.250 1.4924 0.02954 0.02505 -0.0457 0.0012 1.0000
12.500 1.4968 0.03109 0.02675 -0.0432 0.0012 1.0000
12.750 1.4970 0.03284 0.02864 -0.0405 0.0012 1.0000
13.000 1.4944 0.03498 0.03094 -0.0383 0.0012 1.0000
13.250 1.4906 0.03751 0.03363 -0.0368 0.0011 1.0000
13.500 1.4841 0.04070 0.03699 -0.0362 0.0011 1.0000
13.750 1.4766 0.04444 0.04090 -0.0365 0.0011 1.0000
14.000 1.4662 0.04909 0.04572 -0.0379 0.0011 1.0000
14.250 1.4533 0.05463 0.05144 -0.0403 0.0011 1.0000
14.500 1.4380 0.06111 0.05810 -0.0437 0.0011 1.0000
14.750 1.4186 0.06875 0.06590 -0.0479 0.0011 1.0000
15.000 1.3957 0.07735 0.07467 -0.0526 0.0011 1.0000
15.250 1.3697 0.08675 0.08422 -0.0576 0.0011 1.0000
15.500 1.3411 0.09671 0.09432 -0.0626 0.0011 1.0000
15.750 1.3123 0.10690 0.10464 -0.0676 0.0012 1.0000
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Polar data table (+)
Polar graphs
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