NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 100,000 Max Cl/Cd: 58.2 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a410-il-100000.txt Download as CSV file: xf-naca64a410-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3358 0.09349 0.08891 -0.0400 1.0000 0.1063
-9.000 -0.3580 0.09116 0.08672 -0.0415 1.0000 0.1079
-8.750 -0.3815 0.08896 0.08463 -0.0421 1.0000 0.1084
-8.500 -0.3514 0.08404 0.07965 -0.0376 1.0000 0.1133
-8.250 -0.3580 0.08148 0.07715 -0.0361 1.0000 0.1168
-8.000 -0.3758 0.07914 0.07490 -0.0352 1.0000 0.1196
-7.750 -0.4026 0.07722 0.07310 -0.0340 1.0000 0.1209
-7.500 -0.4760 0.08218 0.07781 -0.0353 1.0000 0.1134
-7.250 -0.4847 0.07951 0.07520 -0.0348 1.0000 0.1167
-7.000 -0.5026 0.07604 0.07172 -0.0380 1.0000 0.1205
-6.750 -0.5186 0.07186 0.06741 -0.0411 1.0000 0.1235
-6.500 -0.5070 0.06941 0.06512 -0.0362 1.0000 0.1277
-6.250 -0.5176 0.06576 0.06111 -0.0411 1.0000 0.1373
-6.000 -0.5067 0.06259 0.05816 -0.0370 1.0000 0.1412
-5.750 -0.5037 0.05907 0.05446 -0.0386 1.0000 0.1532
-5.500 -0.4961 0.05617 0.05144 -0.0388 1.0000 0.1669
-5.250 -0.4863 0.05337 0.04859 -0.0382 1.0000 0.1814
-5.000 -0.4751 0.05065 0.04586 -0.0373 1.0000 0.1969
-4.750 -0.4625 0.04812 0.04333 -0.0363 1.0000 0.2138
-4.500 -0.3997 0.03769 0.03044 -0.0445 1.0000 0.0948
-4.250 -0.3692 0.03250 0.02480 -0.0453 1.0000 0.0804
-4.000 -0.3402 0.02929 0.02112 -0.0456 1.0000 0.0746
-3.750 -0.3107 0.02711 0.01819 -0.0453 1.0000 0.0711
-3.500 -0.2856 0.02554 0.01653 -0.0454 1.0000 0.0740
-3.250 -0.2606 0.02447 0.01530 -0.0452 1.0000 0.0774
-3.000 -0.2289 0.02325 0.01388 -0.0458 0.9987 0.0797
-2.750 -0.1868 0.02217 0.01279 -0.0487 0.9948 0.0863
-2.500 -0.1474 0.02147 0.01209 -0.0512 0.9898 0.0992
-2.250 -0.1055 0.02058 0.01130 -0.0543 0.9855 0.1252
-2.000 -0.0691 0.01773 0.01106 -0.0561 0.9845 0.6849
-1.750 -0.0447 0.01783 0.01131 -0.0542 0.9772 0.7950
-1.500 -0.0178 0.01784 0.01143 -0.0528 0.9711 0.8695
-1.250 0.0169 0.01780 0.01140 -0.0540 0.9616 1.0000
-1.000 0.0645 0.01818 0.01147 -0.0590 0.9563 1.0000
-0.750 0.0976 0.01844 0.01154 -0.0612 0.9473 1.0000
-0.500 0.1431 0.01881 0.01170 -0.0655 0.9420 1.0000
-0.250 0.1730 0.01911 0.01185 -0.0669 0.9326 1.0000
0.000 0.2175 0.01944 0.01204 -0.0707 0.9274 1.0000
0.250 0.2445 0.01978 0.01228 -0.0714 0.9177 1.0000
0.500 0.2888 0.02006 0.01248 -0.0750 0.9128 1.0000
0.750 0.3147 0.02039 0.01275 -0.0753 0.9024 1.0000
1.000 0.3506 0.02063 0.01295 -0.0771 0.8942 1.0000
1.250 0.3899 0.02073 0.01303 -0.0794 0.8859 1.0000
1.500 0.4207 0.02091 0.01319 -0.0802 0.8753 1.0000
1.750 0.4720 0.02064 0.01295 -0.0841 0.8694 1.0000
2.000 0.4973 0.02085 0.01320 -0.0838 0.8579 1.0000
2.250 0.5267 0.02105 0.01343 -0.0842 0.8490 1.0000
2.500 0.5628 0.02103 0.01347 -0.0855 0.8425 1.0000
2.750 0.5888 0.02125 0.01375 -0.0852 0.8323 1.0000
3.000 0.6306 0.02081 0.01343 -0.0869 0.8266 1.0000
3.250 0.6556 0.02091 0.01362 -0.0862 0.8151 1.0000
3.500 0.6835 0.02091 0.01373 -0.0858 0.8049 1.0000
3.750 0.7235 0.02020 0.01319 -0.0867 0.7980 1.0000
4.000 0.7587 0.01911 0.01222 -0.0859 0.7835 1.0000
4.250 0.7855 0.01828 0.01151 -0.0838 0.7629 1.0000
4.500 0.8207 0.01695 0.01029 -0.0825 0.7415 1.0000
4.750 0.8464 0.01640 0.00983 -0.0805 0.7157 1.0000
5.000 0.8719 0.01599 0.00951 -0.0786 0.6864 1.0000
5.250 0.8941 0.01564 0.00918 -0.0760 0.6411 1.0000
5.500 0.9091 0.01562 0.00893 -0.0721 0.5478 1.0000
5.750 0.9011 0.01779 0.00937 -0.0653 0.2682 1.0000
6.000 0.8949 0.02099 0.01128 -0.0605 0.1286 1.0000
6.250 0.9025 0.02298 0.01304 -0.0572 0.0998 1.0000
6.500 0.9192 0.02420 0.01424 -0.0553 0.0834 1.0000
6.750 0.9371 0.02544 0.01541 -0.0536 0.0745 1.0000
7.000 0.9594 0.02703 0.01703 -0.0524 0.0695 1.0000
7.250 0.9844 0.02868 0.01864 -0.0518 0.0648 1.0000
7.500 1.0141 0.03097 0.02099 -0.0519 0.0607 1.0000
7.750 1.0456 0.03349 0.02375 -0.0520 0.0589 1.0000
8.000 1.0741 0.03644 0.02704 -0.0515 0.0584 1.0000
8.250 1.0983 0.03983 0.03086 -0.0505 0.0589 1.0000
8.500 1.1172 0.04337 0.03489 -0.0489 0.0593 1.0000
8.750 1.1309 0.04686 0.03884 -0.0467 0.0591 1.0000
9.000 1.1415 0.05082 0.04323 -0.0445 0.0599 1.0000
9.250 1.1537 0.05591 0.04854 -0.0431 0.0620 1.0000
9.500 1.1451 0.06189 0.05544 -0.0381 0.0717 1.0000
9.750 1.0791 0.06163 0.05579 -0.0281 0.0861 1.0000
10.000 1.0232 0.06371 0.05859 -0.0199 0.0892 1.0000
10.250 0.9835 0.06802 0.06315 -0.0156 0.0914 1.0000
10.500 0.9494 0.07289 0.06816 -0.0134 0.0929 1.0000
10.750 0.9186 0.07846 0.07385 -0.0126 0.0950 1.0000
11.000 0.8850 0.08439 0.07988 -0.0130 0.0955 1.0000
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Polar data table (+)
Polar graphs
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