AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 500,000 Max Cl/Cd: 84 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag25-il-500000-n5.txt Download as CSV file: xf-ag25-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5218 0.08596 0.08380 -0.0054 1.0000 0.0048
-8.250 -0.5211 0.08136 0.07923 -0.0084 1.0000 0.0049
-8.000 -0.5208 0.07650 0.07441 -0.0122 1.0000 0.0049
-7.750 -0.5155 0.07040 0.06833 -0.0193 1.0000 0.0050
-7.500 -0.5059 0.06196 0.05989 -0.0304 1.0000 0.0050
-7.250 -0.5065 0.03364 0.03087 -0.0550 1.0000 0.0048
-7.000 -0.4916 0.02619 0.02274 -0.0580 1.0000 0.0049
-6.750 -0.4703 0.02423 0.02053 -0.0582 1.0000 0.0052
-6.500 -0.4482 0.02286 0.01897 -0.0582 1.0000 0.0055
-6.250 -0.4261 0.02141 0.01731 -0.0579 1.0000 0.0059
-6.000 -0.3944 0.01887 0.01435 -0.0597 0.9972 0.0063
-5.750 -0.3606 0.01634 0.01137 -0.0615 0.9944 0.0063
-5.500 -0.3280 0.01458 0.00930 -0.0629 0.9906 0.0065
-5.250 -0.2949 0.01325 0.00774 -0.0641 0.9862 0.0067
-5.000 -0.2609 0.01221 0.00650 -0.0655 0.9822 0.0071
-4.750 -0.2295 0.01146 0.00562 -0.0663 0.9754 0.0075
-4.500 -0.1963 0.01055 0.00458 -0.0676 0.9693 0.0084
-4.250 -0.1655 0.01006 0.00403 -0.0682 0.9604 0.0095
-4.000 -0.1347 0.00968 0.00359 -0.0687 0.9511 0.0110
-3.750 -0.1049 0.00933 0.00316 -0.0690 0.9400 0.0134
-3.500 -0.0765 0.00897 0.00275 -0.0690 0.9272 0.0171
-3.250 -0.0488 0.00870 0.00241 -0.0687 0.9129 0.0225
-3.000 -0.0216 0.00843 0.00215 -0.0684 0.8975 0.0361
-2.750 0.0054 0.00818 0.00192 -0.0681 0.8814 0.0584
-2.500 0.0325 0.00791 0.00172 -0.0679 0.8645 0.0962
-2.250 0.0595 0.00766 0.00155 -0.0677 0.8469 0.1433
-2.000 0.0866 0.00742 0.00142 -0.0675 0.8290 0.1998
-1.750 0.1140 0.00722 0.00132 -0.0674 0.8104 0.2587
-1.500 0.1413 0.00707 0.00123 -0.0672 0.7911 0.3103
-1.250 0.1687 0.00695 0.00117 -0.0671 0.7714 0.3612
-1.000 0.1962 0.00684 0.00112 -0.0670 0.7508 0.4131
-0.750 0.2237 0.00676 0.00109 -0.0668 0.7301 0.4615
-0.500 0.2511 0.00670 0.00106 -0.0667 0.7082 0.5108
-0.250 0.2785 0.00664 0.00106 -0.0665 0.6858 0.5633
0.000 0.3057 0.00657 0.00107 -0.0663 0.6626 0.6220
0.250 0.3325 0.00650 0.00110 -0.0660 0.6384 0.6868
0.500 0.3585 0.00640 0.00114 -0.0655 0.6143 0.7614
0.750 0.3823 0.00629 0.00118 -0.0643 0.5904 0.8433
1.000 0.4084 0.00616 0.00115 -0.0635 0.5647 1.0000
1.250 0.4361 0.00633 0.00119 -0.0634 0.5387 1.0000
1.500 0.4638 0.00652 0.00125 -0.0634 0.5128 1.0000
1.750 0.4914 0.00670 0.00131 -0.0633 0.4870 1.0000
2.000 0.5191 0.00690 0.00139 -0.0633 0.4611 1.0000
2.250 0.5466 0.00710 0.00148 -0.0632 0.4359 1.0000
2.500 0.5741 0.00732 0.00160 -0.0632 0.4113 1.0000
2.750 0.6016 0.00754 0.00172 -0.0631 0.3864 1.0000
3.000 0.6289 0.00778 0.00185 -0.0631 0.3615 1.0000
3.250 0.6563 0.00801 0.00200 -0.0630 0.3374 1.0000
3.500 0.6835 0.00827 0.00218 -0.0629 0.3136 1.0000
3.750 0.7106 0.00854 0.00236 -0.0629 0.2896 1.0000
4.000 0.7376 0.00882 0.00255 -0.0628 0.2654 1.0000
4.250 0.7646 0.00911 0.00276 -0.0627 0.2425 1.0000
4.500 0.7913 0.00942 0.00299 -0.0626 0.2193 1.0000
4.750 0.8180 0.00976 0.00326 -0.0625 0.1965 1.0000
5.000 0.8446 0.01009 0.00353 -0.0623 0.1747 1.0000
5.250 0.8709 0.01047 0.00382 -0.0622 0.1528 1.0000
5.500 0.8972 0.01084 0.00414 -0.0620 0.1330 1.0000
5.750 0.9231 0.01127 0.00451 -0.0618 0.1127 1.0000
6.000 0.9488 0.01173 0.00489 -0.0616 0.0915 1.0000
6.250 0.9744 0.01221 0.00530 -0.0614 0.0735 1.0000
6.500 0.9997 0.01271 0.00574 -0.0611 0.0569 1.0000
6.750 1.0246 0.01327 0.00623 -0.0608 0.0421 1.0000
7.000 1.0494 0.01384 0.00676 -0.0604 0.0301 1.0000
7.250 1.0740 0.01442 0.00734 -0.0601 0.0213 1.0000
7.500 1.0985 0.01501 0.00793 -0.0597 0.0150 1.0000
7.750 1.1229 0.01559 0.00857 -0.0592 0.0113 1.0000
8.000 1.1464 0.01632 0.00933 -0.0587 0.0085 1.0000
8.250 1.1701 0.01700 0.01011 -0.0581 0.0072 1.0000
8.500 1.1933 0.01771 0.01091 -0.0576 0.0062 1.0000
8.750 1.2155 0.01855 0.01182 -0.0569 0.0052 1.0000
9.000 1.2370 0.01947 0.01286 -0.0562 0.0045 1.0000
9.250 1.2589 0.02027 0.01380 -0.0555 0.0041 1.0000
9.500 1.2797 0.02120 0.01485 -0.0546 0.0038 1.0000
9.750 1.2997 0.02218 0.01597 -0.0538 0.0035 1.0000
10.000 1.3189 0.02321 0.01712 -0.0528 0.0033 1.0000
10.250 1.3370 0.02433 0.01836 -0.0518 0.0031 1.0000
10.500 1.3528 0.02567 0.01984 -0.0505 0.0029 1.0000
10.750 1.3637 0.02751 0.02187 -0.0488 0.0027 1.0000
11.000 1.3724 0.02946 0.02402 -0.0468 0.0026 1.0000
11.250 1.3828 0.03104 0.02578 -0.0451 0.0025 1.0000
11.500 1.3892 0.03278 0.02771 -0.0431 0.0024 1.0000
11.750 1.3901 0.03468 0.02982 -0.0405 0.0024 1.0000
12.000 1.3881 0.03689 0.03223 -0.0382 0.0023 1.0000
12.250 1.3841 0.03953 0.03506 -0.0366 0.0023 1.0000
12.500 1.3782 0.04268 0.03841 -0.0358 0.0023 1.0000
12.750 1.3705 0.04645 0.04238 -0.0359 0.0022 1.0000
13.000 1.3608 0.05093 0.04707 -0.0371 0.0022 1.0000
13.250 1.3494 0.05619 0.05253 -0.0392 0.0022 1.0000
13.500 1.3356 0.06232 0.05885 -0.0423 0.0022 1.0000
13.750 1.3202 0.06918 0.06591 -0.0461 0.0022 1.0000
14.000 1.3024 0.07685 0.07375 -0.0505 0.0022 1.0000
14.250 1.2830 0.08507 0.08213 -0.0551 0.0022 1.0000
14.500 1.2622 0.09369 0.09090 -0.0597 0.0022 1.0000
14.750 1.2404 0.10269 0.10003 -0.0644 0.0022 1.0000
15.000 1.2185 0.11193 0.10939 -0.0692 0.0023 1.0000
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Polar data table (+)
Polar graphs
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