AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 50,000 Max Cl/Cd: 34.4 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3024-il-50000.txt Download as CSV file: xf-s3024-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL 3024 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3355 0.10218 0.09577 -0.0299 1.0000 0.2178
-8.000 -0.3360 0.10012 0.09379 -0.0284 1.0000 0.2273
-7.750 -0.3379 0.09753 0.09131 -0.0268 1.0000 0.2346
-7.500 -0.3532 0.09678 0.09070 -0.0244 1.0000 0.2431
-7.250 -0.3538 0.09407 0.08807 -0.0220 1.0000 0.2502
-7.000 -0.3727 0.09351 0.08765 -0.0186 1.0000 0.2576
-6.750 -0.4097 0.09416 0.08850 -0.0157 1.0000 0.2598
-6.500 -0.3988 0.09061 0.08497 -0.0123 1.0000 0.2725
-6.250 -0.4033 0.08818 0.08263 -0.0096 1.0000 0.2817
-6.000 -0.4360 0.08825 0.08284 -0.0090 1.0000 0.2902
-5.750 -0.4297 0.08509 0.07972 -0.0054 1.0000 0.3037
-5.500 -0.4290 0.08242 0.07711 -0.0024 1.0000 0.3155
-5.250 -0.4344 0.08016 0.07492 0.0000 1.0000 0.3298
-5.000 -0.4400 0.07801 0.07284 0.0022 1.0000 0.3466
-4.750 -0.4513 0.07622 0.07112 0.0034 1.0000 0.3673
-4.500 -0.4460 0.07339 0.06835 0.0076 1.0000 0.3860
-3.500 -0.3181 0.04316 0.03535 -0.0397 1.0000 0.1232
-3.250 -0.2931 0.03978 0.03150 -0.0404 1.0000 0.1174
-3.000 -0.2674 0.03704 0.02821 -0.0407 1.0000 0.1166
-2.750 -0.2428 0.03496 0.02568 -0.0406 1.0000 0.1184
-2.500 -0.2176 0.03304 0.02331 -0.0403 1.0000 0.1200
-2.250 -0.1921 0.03139 0.02116 -0.0398 1.0000 0.1234
-2.000 -0.1686 0.03005 0.01967 -0.0393 1.0000 0.1343
-1.750 -0.1446 0.02893 0.01839 -0.0386 1.0000 0.1507
-1.500 -0.1206 0.02788 0.01732 -0.0379 1.0000 0.1860
-1.250 -0.0924 0.02633 0.01638 -0.0379 1.0000 0.3045
-1.000 -0.0651 0.02289 0.01537 -0.0358 1.0000 1.0000
-0.750 -0.0442 0.02338 0.01526 -0.0355 1.0000 1.0000
-0.500 -0.0243 0.02391 0.01536 -0.0351 1.0000 1.0000
-0.250 -0.0050 0.02449 0.01556 -0.0348 1.0000 1.0000
0.000 0.0140 0.02511 0.01588 -0.0346 1.0000 1.0000
0.250 0.0327 0.02578 0.01629 -0.0343 1.0000 1.0000
0.500 0.0658 0.02690 0.01712 -0.0369 0.9940 1.0000
0.750 0.1103 0.02828 0.01820 -0.0415 0.9804 1.0000
1.000 0.1523 0.02960 0.01930 -0.0456 0.9663 1.0000
1.250 0.1922 0.03085 0.02036 -0.0492 0.9520 1.0000
1.500 0.2307 0.03205 0.02139 -0.0524 0.9372 1.0000
1.750 0.2678 0.03320 0.02242 -0.0552 0.9222 1.0000
2.000 0.3042 0.03431 0.02343 -0.0578 0.9067 1.0000
2.250 0.3395 0.03537 0.02442 -0.0601 0.8913 1.0000
2.500 0.3757 0.03639 0.02539 -0.0623 0.8753 1.0000
2.750 0.4123 0.03736 0.02633 -0.0645 0.8592 1.0000
3.000 0.4498 0.03825 0.02722 -0.0666 0.8431 1.0000
3.250 0.4794 0.03908 0.02805 -0.0674 0.8262 1.0000
3.500 0.5061 0.03989 0.02888 -0.0678 0.8087 1.0000
3.750 0.5363 0.04064 0.02969 -0.0685 0.7913 1.0000
4.000 0.5694 0.04129 0.03040 -0.0694 0.7742 1.0000
4.250 0.6051 0.04179 0.03097 -0.0704 0.7575 1.0000
4.500 0.6444 0.04206 0.03138 -0.0716 0.7409 1.0000
4.750 0.6710 0.04260 0.03200 -0.0712 0.7228 1.0000
5.000 0.6962 0.04311 0.03262 -0.0706 0.7038 1.0000
5.250 0.7322 0.04310 0.03275 -0.0708 0.6863 1.0000
5.500 0.7749 0.04253 0.03240 -0.0712 0.6695 1.0000
5.750 0.8256 0.04117 0.03127 -0.0717 0.6535 1.0000
6.000 0.8495 0.04127 0.03154 -0.0701 0.6336 1.0000
6.250 0.8881 0.04020 0.03068 -0.0691 0.6152 1.0000
6.500 0.9414 0.03790 0.02861 -0.0688 0.5974 1.0000
6.750 0.9870 0.03609 0.02705 -0.0679 0.5767 1.0000
7.000 1.0297 0.03453 0.02564 -0.0669 0.5530 1.0000
7.250 1.0616 0.03390 0.02516 -0.0653 0.5266 1.0000
7.500 1.0938 0.03337 0.02469 -0.0637 0.4986 1.0000
7.750 1.1223 0.03325 0.02460 -0.0621 0.4693 1.0000
8.000 1.1474 0.03350 0.02485 -0.0603 0.4396 1.0000
8.250 1.1701 0.03401 0.02537 -0.0584 0.4096 1.0000
8.500 1.1907 0.03479 0.02613 -0.0564 0.3802 1.0000
8.750 1.2095 0.03581 0.02714 -0.0544 0.3516 1.0000
9.000 1.2266 0.03697 0.02829 -0.0523 0.3234 1.0000
9.250 1.2427 0.03830 0.02960 -0.0502 0.2962 1.0000
9.500 1.2580 0.03973 0.03101 -0.0481 0.2692 1.0000
9.750 1.2716 0.04126 0.03246 -0.0458 0.2421 1.0000
10.000 1.2800 0.04272 0.03382 -0.0430 0.2143 1.0000
10.250 1.2806 0.04379 0.03470 -0.0396 0.1869 1.0000
10.500 1.2726 0.04535 0.03637 -0.0355 0.1648 1.0000
10.750 1.2707 0.04747 0.03837 -0.0322 0.1427 1.0000
11.000 1.2688 0.05010 0.04103 -0.0290 0.1250 1.0000
11.250 1.2700 0.05300 0.04400 -0.0263 0.1118 1.0000
11.500 1.2744 0.05648 0.04766 -0.0243 0.1029 1.0000
11.750 1.2780 0.06001 0.05143 -0.0224 0.0970 1.0000
12.000 1.2815 0.06409 0.05566 -0.0209 0.0928 1.0000
12.250 1.2647 0.06792 0.05989 -0.0183 0.0919 1.0000
12.500 1.2449 0.07222 0.06454 -0.0165 0.0912 1.0000
12.750 1.2230 0.07696 0.06957 -0.0156 0.0911 1.0000
13.000 1.1993 0.08223 0.07510 -0.0156 0.0914 1.0000
13.250 1.1738 0.08821 0.08129 -0.0166 0.0920 1.0000
13.500 1.1477 0.09490 0.08816 -0.0187 0.0927 1.0000
13.750 1.1247 0.10209 0.09548 -0.0215 0.0935 1.0000
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Polar data table (+)
Polar graphs
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