AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 500,000 Max Cl/Cd: 83.92 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag24-il-500000-n5.txt Download as CSV file: xf-ag24-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5400 0.08301 0.08088 -0.0100 1.0000 0.0054
-8.500 -0.5441 0.07703 0.07494 -0.0142 1.0000 0.0054
-8.250 -0.5498 0.06979 0.06774 -0.0210 1.0000 0.0053
-8.000 -0.5913 0.03180 0.02876 -0.0553 1.0000 0.0049
-7.750 -0.5759 0.02774 0.02427 -0.0564 1.0000 0.0051
-7.500 -0.5569 0.02539 0.02163 -0.0565 1.0000 0.0054
-7.250 -0.5377 0.02303 0.01893 -0.0563 1.0000 0.0057
-7.000 -0.5176 0.02078 0.01634 -0.0559 1.0000 0.0060
-6.750 -0.4904 0.01844 0.01360 -0.0567 0.9981 0.0062
-6.500 -0.4578 0.01653 0.01136 -0.0583 0.9951 0.0063
-6.250 -0.4254 0.01509 0.00965 -0.0597 0.9919 0.0066
-6.000 -0.3930 0.01402 0.00839 -0.0609 0.9877 0.0068
-5.750 -0.3600 0.01280 0.00700 -0.0624 0.9837 0.0073
-5.500 -0.3283 0.01201 0.00613 -0.0634 0.9783 0.0080
-5.250 -0.2961 0.01148 0.00553 -0.0645 0.9723 0.0088
-5.000 -0.2644 0.01097 0.00494 -0.0653 0.9659 0.0097
-4.750 -0.2338 0.01061 0.00450 -0.0659 0.9577 0.0108
-4.500 -0.2044 0.01006 0.00390 -0.0663 0.9485 0.0131
-4.250 -0.1754 0.00972 0.00349 -0.0664 0.9385 0.0153
-4.000 -0.1473 0.00940 0.00309 -0.0663 0.9273 0.0181
-3.750 -0.1199 0.00910 0.00277 -0.0661 0.9147 0.0243
-3.500 -0.0927 0.00883 0.00247 -0.0658 0.9016 0.0357
-3.250 -0.0656 0.00855 0.00222 -0.0656 0.8877 0.0561
-3.000 -0.0385 0.00826 0.00201 -0.0654 0.8734 0.0891
-2.750 -0.0113 0.00798 0.00182 -0.0652 0.8586 0.1313
-2.500 0.0159 0.00771 0.00165 -0.0651 0.8435 0.1814
-2.250 0.0434 0.00747 0.00152 -0.0651 0.8276 0.2350
-2.000 0.0709 0.00728 0.00141 -0.0650 0.8111 0.2844
-1.750 0.0985 0.00713 0.00133 -0.0649 0.7941 0.3290
-1.500 0.1261 0.00701 0.00125 -0.0648 0.7765 0.3754
-1.250 0.1537 0.00691 0.00119 -0.0647 0.7583 0.4194
-1.000 0.1815 0.00682 0.00115 -0.0646 0.7392 0.4615
-0.750 0.2091 0.00676 0.00112 -0.0645 0.7196 0.5033
-0.500 0.2368 0.00671 0.00110 -0.0644 0.6993 0.5458
-0.250 0.2643 0.00667 0.00110 -0.0643 0.6780 0.5893
0.000 0.2917 0.00664 0.00111 -0.0642 0.6562 0.6328
0.250 0.3189 0.00662 0.00114 -0.0639 0.6338 0.6780
0.500 0.3459 0.00660 0.00118 -0.0636 0.6110 0.7253
0.750 0.3723 0.00661 0.00123 -0.0632 0.5881 0.7733
1.000 0.3979 0.00662 0.00129 -0.0626 0.5652 0.8198
1.250 0.4225 0.00662 0.00134 -0.0616 0.5424 0.8672
1.500 0.4454 0.00661 0.00137 -0.0602 0.5204 0.9268
1.750 0.4767 0.00670 0.00138 -0.0609 0.4966 1.0000
2.000 0.5046 0.00688 0.00146 -0.0609 0.4729 1.0000
2.250 0.5323 0.00708 0.00156 -0.0609 0.4503 1.0000
2.500 0.5601 0.00727 0.00166 -0.0610 0.4278 1.0000
2.750 0.5878 0.00748 0.00177 -0.0610 0.4054 1.0000
3.000 0.6154 0.00770 0.00190 -0.0610 0.3830 1.0000
3.250 0.6429 0.00792 0.00205 -0.0610 0.3605 1.0000
3.500 0.6703 0.00816 0.00220 -0.0609 0.3382 1.0000
3.750 0.6976 0.00841 0.00237 -0.0609 0.3152 1.0000
4.000 0.7249 0.00867 0.00256 -0.0609 0.2925 1.0000
4.250 0.7519 0.00896 0.00278 -0.0608 0.2688 1.0000
4.750 0.8056 0.00960 0.00324 -0.0607 0.2205 1.0000
5.000 0.8322 0.00994 0.00350 -0.0606 0.1976 1.0000
5.250 0.8585 0.01032 0.00379 -0.0604 0.1737 1.0000
5.500 0.8847 0.01073 0.00413 -0.0603 0.1501 1.0000
5.750 0.9108 0.01113 0.00446 -0.0601 0.1290 1.0000
6.000 0.9364 0.01162 0.00484 -0.0599 0.1040 1.0000
6.250 0.9617 0.01214 0.00526 -0.0597 0.0822 1.0000
6.500 0.9869 0.01266 0.00570 -0.0594 0.0629 1.0000
6.750 1.0117 0.01323 0.00621 -0.0591 0.0458 1.0000
7.000 1.0365 0.01379 0.00672 -0.0588 0.0328 1.0000
7.250 1.0612 0.01436 0.00727 -0.0585 0.0236 1.0000
7.500 1.0855 0.01496 0.00786 -0.0581 0.0165 1.0000
7.750 1.1093 0.01562 0.00852 -0.0576 0.0116 1.0000
8.000 1.1337 0.01617 0.00914 -0.0572 0.0096 1.0000
8.250 1.1569 0.01689 0.00993 -0.0566 0.0078 1.0000
8.500 1.1798 0.01765 0.01078 -0.0560 0.0068 1.0000
8.750 1.2026 0.01837 0.01161 -0.0554 0.0061 1.0000
9.000 1.2247 0.01915 0.01249 -0.0547 0.0055 1.0000
9.250 1.2461 0.02000 0.01342 -0.0540 0.0050 1.0000
9.500 1.2643 0.02125 0.01479 -0.0529 0.0044 1.0000
9.750 1.2847 0.02210 0.01576 -0.0520 0.0041 1.0000
10.000 1.3044 0.02301 0.01678 -0.0511 0.0039 1.0000
10.250 1.3221 0.02410 0.01801 -0.0500 0.0037 1.0000
10.500 1.3385 0.02528 0.01935 -0.0488 0.0035 1.0000
10.750 1.3537 0.02651 0.02072 -0.0474 0.0033 1.0000
11.000 1.3674 0.02780 0.02215 -0.0460 0.0032 1.0000
11.250 1.3793 0.02916 0.02364 -0.0444 0.0030 1.0000
11.500 1.3885 0.03057 0.02520 -0.0425 0.0029 1.0000
11.750 1.3933 0.03210 0.02687 -0.0402 0.0028 1.0000
12.000 1.3953 0.03389 0.02880 -0.0380 0.0028 1.0000
12.250 1.3949 0.03602 0.03108 -0.0361 0.0027 1.0000
12.500 1.3913 0.03867 0.03389 -0.0348 0.0026 1.0000
12.750 1.3848 0.04193 0.03735 -0.0341 0.0026 1.0000
13.000 1.3758 0.04586 0.04146 -0.0342 0.0025 1.0000
13.250 1.3647 0.05049 0.04630 -0.0352 0.0025 1.0000
14.000 1.3226 0.06830 0.06467 -0.0431 0.0024 1.0000
14.250 1.3077 0.07503 0.07158 -0.0465 0.0024 1.0000
14.500 1.2898 0.08255 0.07925 -0.0505 0.0024 1.0000
14.750 1.2710 0.09038 0.08724 -0.0545 0.0024 1.0000
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Polar data table (+)
Polar graphs
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