AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 200,000 Max Cl/Cd: 65.29 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag27-il-200000-n5.txt Download as CSV file: xf-ag27-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG27 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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3992 0.11038 0.10700 0.0010 1.0000 0.0201
-9.500 -0.3961 0.10694 0.10357 0.0001 1.0000 0.0213
-9.000 -0.5124 0.11002 0.10651 0.0070 1.0000 0.0174
-8.750 -0.5021 0.10741 0.10390 0.0090 1.0000 0.0192
-8.500 -0.4958 0.10425 0.10076 0.0077 1.0000 0.0204
-8.250 -0.4902 0.10085 0.09739 0.0059 1.0000 0.0215
-8.000 -0.4849 0.09732 0.09389 0.0039 1.0000 0.0222
-7.750 -0.4797 0.09373 0.09033 0.0017 1.0000 0.0229
-7.500 -0.4745 0.09012 0.08675 -0.0012 1.0000 0.0236
-7.250 -0.4643 0.08610 0.08278 -0.0083 1.0000 0.0250
-7.000 -0.4500 0.08165 0.07834 -0.0143 1.0000 0.0253
-6.750 -0.4346 0.07694 0.07361 -0.0198 1.0000 0.0253
-6.250 -0.4140 0.06511 0.06176 -0.0265 1.0000 0.0155
-6.000 -0.3950 0.05982 0.05644 -0.0323 1.0000 0.0146
-5.750 -0.3715 0.05337 0.04989 -0.0393 1.0000 0.0136
-5.500 -0.3422 0.04413 0.04040 -0.0481 1.0000 0.0123
-5.000 -0.2827 0.02787 0.02289 -0.0571 1.0000 0.0109
-4.500 -0.2299 0.02031 0.01415 -0.0590 1.0000 0.0113
-4.250 -0.2041 0.01826 0.01175 -0.0590 1.0000 0.0119
-4.000 -0.1787 0.01709 0.01038 -0.0587 1.0000 0.0130
-3.750 -0.1535 0.01631 0.00942 -0.0583 1.0000 0.0152
-3.500 -0.1275 0.01514 0.00801 -0.0578 1.0000 0.0163
-3.250 -0.1013 0.01394 0.00662 -0.0574 1.0000 0.0172
-3.000 -0.0675 0.01278 0.00537 -0.0588 0.9963 0.0196
-2.750 -0.0306 0.01218 0.00469 -0.0607 0.9900 0.0246
-2.500 0.0070 0.01146 0.00390 -0.0627 0.9835 0.0335
-2.250 0.0424 0.01091 0.00336 -0.0643 0.9743 0.0541
-2.000 0.0778 0.01040 0.00302 -0.0659 0.9645 0.1008
-1.750 0.1127 0.00991 0.00279 -0.0675 0.9535 0.1773
-1.500 0.1462 0.00948 0.00264 -0.0688 0.9404 0.2688
-1.250 0.1778 0.00912 0.00252 -0.0695 0.9250 0.3609
-1.000 0.2077 0.00876 0.00243 -0.0698 0.9077 0.4578
-0.750 0.2354 0.00836 0.00235 -0.0694 0.8890 0.5691
-0.500 0.2565 0.00768 0.00227 -0.0672 0.8695 0.7734
-0.250 0.2871 0.00738 0.00208 -0.0669 0.8479 1.0000
0.000 0.3139 0.00746 0.00200 -0.0663 0.8253 1.0000
0.250 0.3404 0.00755 0.00193 -0.0656 0.8017 1.0000
0.500 0.3669 0.00766 0.00188 -0.0650 0.7765 1.0000
0.750 0.3934 0.00779 0.00185 -0.0644 0.7504 1.0000
1.000 0.4198 0.00794 0.00184 -0.0637 0.7229 1.0000
1.250 0.4462 0.00811 0.00185 -0.0632 0.6941 1.0000
1.500 0.4726 0.00830 0.00189 -0.0626 0.6641 1.0000
1.750 0.4990 0.00850 0.00193 -0.0621 0.6331 1.0000
2.000 0.5255 0.00872 0.00200 -0.0616 0.6010 1.0000
2.250 0.5519 0.00896 0.00208 -0.0612 0.5682 1.0000
2.500 0.5782 0.00922 0.00219 -0.0608 0.5344 1.0000
2.750 0.6046 0.00950 0.00235 -0.0604 0.4995 1.0000
3.000 0.6308 0.00980 0.00250 -0.0600 0.4645 1.0000
3.250 0.6570 0.01013 0.00268 -0.0596 0.4276 1.0000
3.500 0.6831 0.01048 0.00289 -0.0593 0.3907 1.0000
3.750 0.7091 0.01086 0.00316 -0.0590 0.3532 1.0000
4.000 0.7350 0.01127 0.00343 -0.0587 0.3165 1.0000
4.250 0.7609 0.01169 0.00373 -0.0584 0.2815 1.0000
4.500 0.7866 0.01215 0.00406 -0.0582 0.2475 1.0000
4.750 0.8123 0.01261 0.00446 -0.0579 0.2179 1.0000
5.000 0.8379 0.01309 0.00486 -0.0576 0.1905 1.0000
5.250 0.8634 0.01358 0.00528 -0.0573 0.1667 1.0000
5.500 0.8889 0.01407 0.00575 -0.0570 0.1476 1.0000
5.750 0.9143 0.01458 0.00624 -0.0567 0.1292 1.0000
6.000 0.9395 0.01511 0.00679 -0.0564 0.1140 1.0000
6.250 0.9645 0.01566 0.00735 -0.0560 0.1002 1.0000
6.500 0.9894 0.01623 0.00795 -0.0557 0.0875 1.0000
6.750 1.0141 0.01682 0.00859 -0.0553 0.0765 1.0000
7.000 1.0386 0.01745 0.00926 -0.0548 0.0658 1.0000
7.250 1.0625 0.01815 0.01004 -0.0543 0.0564 1.0000
7.500 1.0861 0.01891 0.01083 -0.0539 0.0466 1.0000
7.750 1.1094 0.01970 0.01167 -0.0533 0.0378 1.0000
8.000 1.1324 0.02053 0.01263 -0.0527 0.0307 1.0000
8.250 1.1541 0.02159 0.01376 -0.0520 0.0245 1.0000
8.500 1.1754 0.02267 0.01494 -0.0513 0.0196 1.0000
8.750 1.1948 0.02411 0.01655 -0.0503 0.0166 1.0000
9.000 1.2153 0.02523 0.01788 -0.0495 0.0138 1.0000
9.250 1.2313 0.02704 0.01981 -0.0483 0.0117 1.0000
9.500 1.2485 0.02865 0.02169 -0.0471 0.0107 1.0000
9.750 1.2636 0.03050 0.02379 -0.0458 0.0098 1.0000
10.000 1.2771 0.03247 0.02600 -0.0444 0.0091 1.0000
10.250 1.2889 0.03452 0.02828 -0.0429 0.0085 1.0000
10.500 1.2985 0.03659 0.03055 -0.0415 0.0080 1.0000
10.750 1.3009 0.03940 0.03359 -0.0397 0.0075 1.0000
11.000 1.3015 0.04216 0.03665 -0.0378 0.0071 1.0000
11.250 1.2996 0.04464 0.03941 -0.0357 0.0068 1.0000
11.500 1.2938 0.04762 0.04266 -0.0343 0.0065 1.0000
11.750 1.2848 0.05130 0.04660 -0.0340 0.0063 1.0000
12.000 1.2729 0.05589 0.05144 -0.0351 0.0063 1.0000
12.250 1.2593 0.06142 0.05723 -0.0377 0.0062 1.0000
12.500 1.2437 0.06807 0.06411 -0.0417 0.0062 1.0000
12.750 1.2261 0.07584 0.07209 -0.0469 0.0062 1.0000
13.000 1.2062 0.08471 0.08114 -0.0528 0.0063 1.0000
13.250 1.1843 0.09445 0.09104 -0.0590 0.0065 1.0000
13.500 1.1607 0.10472 0.10142 -0.0650 0.0068 1.0000
13.750 1.1368 0.11520 0.11198 -0.0707 0.0070 1.0000
14.000 1.1137 0.12547 0.12230 -0.0760 0.0073 1.0000
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Polar data table (+)
Polar graphs
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