AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.09 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag24-il-1000000.txt Download as CSV file: xf-ag24-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG24 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5211 0.08459 0.08308 -0.0087 1.0000 0.0084
-8.250 -0.5203 0.07984 0.07835 -0.0121 1.0000 0.0087
-8.000 -0.5207 0.07459 0.07313 -0.0164 1.0000 0.0088
-7.750 -0.5156 0.06737 0.06593 -0.0256 1.0000 0.0090
-7.500 -0.5059 0.05509 0.05357 -0.0421 1.0000 0.0089
-7.250 -0.5013 0.04260 0.04080 -0.0518 1.0000 0.0089
-6.250 -0.4284 0.01613 0.01195 -0.0590 0.9957 0.0071
-6.000 -0.3953 0.01309 0.00853 -0.0610 0.9942 0.0075
-5.750 -0.3624 0.01177 0.00705 -0.0623 0.9915 0.0078
-5.500 -0.3283 0.01075 0.00592 -0.0638 0.9887 0.0081
-5.250 -0.2940 0.01006 0.00516 -0.0653 0.9856 0.0087
-5.000 -0.2593 0.00953 0.00456 -0.0668 0.9824 0.0098
-4.750 -0.2294 0.00914 0.00411 -0.0671 0.9752 0.0106
-4.500 -0.1983 0.00848 0.00332 -0.0678 0.9690 0.0119
-4.250 -0.1711 0.00806 0.00286 -0.0675 0.9591 0.0141
-4.000 -0.1441 0.00787 0.00264 -0.0672 0.9491 0.0165
-3.750 -0.1173 0.00748 0.00220 -0.0667 0.9385 0.0231
-3.500 -0.0908 0.00720 0.00191 -0.0662 0.9269 0.0355
-3.250 -0.0640 0.00687 0.00169 -0.0660 0.9144 0.0675
-3.000 -0.0370 0.00657 0.00150 -0.0658 0.9013 0.1117
-2.750 -0.0098 0.00629 0.00135 -0.0656 0.8878 0.1602
-2.500 0.0176 0.00604 0.00121 -0.0655 0.8738 0.2150
-2.250 0.0451 0.00583 0.00111 -0.0655 0.8593 0.2687
-2.000 0.0728 0.00565 0.00103 -0.0654 0.8443 0.3220
-1.750 0.1006 0.00548 0.00097 -0.0654 0.8289 0.3759
-1.500 0.1285 0.00536 0.00091 -0.0653 0.8126 0.4228
-1.250 0.1565 0.00526 0.00087 -0.0653 0.7956 0.4675
-1.000 0.1844 0.00517 0.00085 -0.0653 0.7779 0.5170
-0.750 0.2123 0.00510 0.00083 -0.0652 0.7595 0.5631
-0.500 0.2402 0.00503 0.00082 -0.0652 0.7402 0.6101
-0.250 0.2680 0.00498 0.00082 -0.0651 0.7199 0.6587
0.000 0.2957 0.00492 0.00084 -0.0650 0.6990 0.7097
0.250 0.3230 0.00489 0.00087 -0.0647 0.6772 0.7612
0.500 0.3499 0.00486 0.00091 -0.0644 0.6547 0.8098
0.750 0.3759 0.00485 0.00095 -0.0638 0.6318 0.8570
1.000 0.3999 0.00482 0.00097 -0.0627 0.6091 0.9082
1.250 0.4276 0.00479 0.00096 -0.0624 0.5852 1.0000
1.500 0.4558 0.00494 0.00100 -0.0625 0.5609 1.0000
1.750 0.4840 0.00511 0.00105 -0.0625 0.5366 1.0000
2.000 0.5121 0.00526 0.00111 -0.0626 0.5124 1.0000
2.250 0.5402 0.00543 0.00119 -0.0627 0.4885 1.0000
2.500 0.5682 0.00561 0.00127 -0.0627 0.4644 1.0000
2.750 0.5961 0.00580 0.00136 -0.0627 0.4402 1.0000
3.000 0.6240 0.00598 0.00146 -0.0628 0.4165 1.0000
3.250 0.6518 0.00619 0.00158 -0.0628 0.3931 1.0000
3.500 0.6795 0.00641 0.00170 -0.0628 0.3688 1.0000
3.750 0.7071 0.00663 0.00183 -0.0628 0.3444 1.0000
4.000 0.7346 0.00686 0.00198 -0.0628 0.3198 1.0000
4.250 0.7619 0.00712 0.00216 -0.0628 0.2944 1.0000
4.500 0.7892 0.00740 0.00233 -0.0627 0.2696 1.0000
4.750 0.8162 0.00770 0.00253 -0.0627 0.2434 1.0000
5.000 0.8430 0.00802 0.00275 -0.0626 0.2165 1.0000
5.250 0.8699 0.00834 0.00298 -0.0626 0.1928 1.0000
5.500 0.8962 0.00875 0.00326 -0.0624 0.1632 1.0000
5.750 0.9226 0.00912 0.00354 -0.0623 0.1392 1.0000
6.000 0.9486 0.00956 0.00386 -0.0621 0.1131 1.0000
6.250 0.9743 0.01003 0.00420 -0.0620 0.0886 1.0000
6.500 0.9999 0.01052 0.00458 -0.0617 0.0667 1.0000
6.750 1.0251 0.01106 0.00502 -0.0615 0.0469 1.0000
7.000 1.0506 0.01155 0.00545 -0.0612 0.0337 1.0000
7.250 1.0756 0.01208 0.00593 -0.0609 0.0225 1.0000
7.500 1.1003 0.01268 0.00648 -0.0605 0.0145 1.0000
7.750 1.1249 0.01330 0.00714 -0.0600 0.0102 1.0000
8.000 1.1479 0.01420 0.00810 -0.0593 0.0073 1.0000
8.250 1.1729 0.01466 0.00862 -0.0590 0.0066 1.0000
8.500 1.1971 0.01521 0.00923 -0.0585 0.0058 1.0000
8.750 1.2206 0.01587 0.00995 -0.0580 0.0053 1.0000
9.000 1.2422 0.01682 0.01100 -0.0572 0.0048 1.0000
9.250 1.2583 0.01858 0.01297 -0.0556 0.0044 1.0000
9.500 1.2800 0.01935 0.01383 -0.0549 0.0043 1.0000
9.750 1.3012 0.02016 0.01474 -0.0541 0.0041 1.0000
10.000 1.3212 0.02109 0.01576 -0.0531 0.0040 1.0000
10.250 1.3398 0.02213 0.01694 -0.0521 0.0038 1.0000
10.500 1.3575 0.02324 0.01816 -0.0509 0.0036 1.0000
10.750 1.3742 0.02437 0.01940 -0.0497 0.0034 1.0000
11.000 1.3896 0.02557 0.02072 -0.0483 0.0032 1.0000
11.250 1.4030 0.02689 0.02215 -0.0468 0.0030 1.0000
11.500 1.4139 0.02833 0.02371 -0.0450 0.0029 1.0000
11.750 1.4195 0.03000 0.02553 -0.0427 0.0028 1.0000
12.000 1.4184 0.03192 0.02759 -0.0397 0.0028 1.0000
12.250 1.4143 0.03421 0.03005 -0.0370 0.0027 1.0000
12.500 1.4071 0.03706 0.03308 -0.0350 0.0027 1.0000
12.750 1.3987 0.04038 0.03658 -0.0339 0.0027 1.0000
13.000 1.3893 0.04420 0.04059 -0.0337 0.0027 1.0000
13.250 1.3790 0.04858 0.04515 -0.0344 0.0027 1.0000
13.500 1.3655 0.05385 0.05061 -0.0361 0.0026 1.0000
13.750 1.3535 0.05935 0.05627 -0.0385 0.0027 1.0000
14.000 1.3380 0.06581 0.06290 -0.0417 0.0027 1.0000
14.250 1.3217 0.07271 0.06997 -0.0453 0.0027 1.0000
14.500 1.3057 0.07987 0.07728 -0.0491 0.0027 1.0000
14.750 1.2869 0.08771 0.08527 -0.0533 0.0027 1.0000
15.000 1.2675 0.09596 0.09365 -0.0577 0.0027 1.0000
15.250 1.2472 0.10466 0.10248 -0.0623 0.0027 1.0000
15.500 1.2250 0.11400 0.11195 -0.0671 0.0028 1.0000
15.750 1.2008 0.12422 0.12231 -0.0725 0.0028 1.0000
16.000 1.1728 0.13573 0.13397 -0.0785 0.0029 1.0000
16.250 1.1383 0.14978 0.14818 -0.0859 0.0030 1.0000
16.500 1.0757 0.17447 0.17308 -0.0988 0.0033 1.0000
16.750 0.8740 0.14894 0.14750 -0.0634 0.0035 1.0000
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Polar data table (+)
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