NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 500,000 Max Cl/Cd: 100.72 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a410-il-500000.txt Download as CSV file: xf-naca64a410-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4386 0.08360 0.08140 -0.0473 1.0000 0.0186
-9.000 -0.4481 0.07985 0.07770 -0.0475 1.0000 0.0189
-8.750 -0.4686 0.07771 0.07563 -0.0449 1.0000 0.0189
-8.500 -0.4779 0.07386 0.07182 -0.0471 0.9978 0.0190
-8.250 -0.4609 0.06567 0.06356 -0.0610 0.9928 0.0193
-8.000 -0.4448 0.06049 0.05830 -0.0679 0.9883 0.0197
-7.750 -0.4242 0.05557 0.05326 -0.0746 0.9852 0.0205
-7.500 -0.4023 0.05033 0.04784 -0.0807 0.9821 0.0218
-7.250 -0.3744 0.04526 0.04230 -0.0851 0.9766 0.0248
-6.250 -0.2957 0.02083 0.01578 -0.0919 0.9595 0.0194
-6.000 -0.2669 0.01886 0.01355 -0.0926 0.9568 0.0198
-5.750 -0.2419 0.01839 0.01305 -0.0925 0.9521 0.0213
-5.500 -0.2164 0.01686 0.01129 -0.0920 0.9473 0.0219
-5.250 -0.1889 0.01542 0.00964 -0.0919 0.9437 0.0225
-5.000 -0.1627 0.01439 0.00847 -0.0915 0.9397 0.0233
-4.750 -0.1380 0.01361 0.00758 -0.0908 0.9341 0.0241
-4.500 -0.1120 0.01277 0.00664 -0.0904 0.9298 0.0256
-4.250 -0.0876 0.01179 0.00562 -0.0898 0.9252 0.0273
-4.000 -0.0627 0.01129 0.00510 -0.0892 0.9193 0.0290
-3.750 -0.0366 0.01083 0.00458 -0.0887 0.9140 0.0312
-3.500 -0.0111 0.01055 0.00425 -0.0881 0.9071 0.0335
-3.250 0.0138 0.00986 0.00351 -0.0875 0.9005 0.0387
-3.000 0.0400 0.00957 0.00317 -0.0871 0.8942 0.0443
-2.750 0.0662 0.00912 0.00266 -0.0867 0.8880 0.0565
-2.500 0.0928 0.00873 0.00246 -0.0865 0.8826 0.1148
-2.250 0.1191 0.00847 0.00228 -0.0863 0.8755 0.1447
-2.000 0.1439 0.00769 0.00205 -0.0862 0.8698 0.3170
-1.750 0.1673 0.00698 0.00199 -0.0857 0.8619 0.5197
-1.500 0.1937 0.00679 0.00193 -0.0853 0.8552 0.5833
-1.250 0.2197 0.00666 0.00192 -0.0849 0.8463 0.6277
-1.000 0.2465 0.00659 0.00185 -0.0845 0.8375 0.6544
-0.750 0.2730 0.00651 0.00182 -0.0841 0.8280 0.6845
-0.500 0.2995 0.00645 0.00182 -0.0837 0.8188 0.7120
-0.250 0.3265 0.00642 0.00179 -0.0834 0.8104 0.7323
0.000 0.3532 0.00638 0.00178 -0.0831 0.8003 0.7532
0.250 0.3801 0.00636 0.00176 -0.0828 0.7900 0.7690
0.500 0.4071 0.00634 0.00173 -0.0826 0.7800 0.7830
1.000 0.4604 0.00629 0.00172 -0.0819 0.7585 0.8140
1.250 0.4864 0.00625 0.00174 -0.0815 0.7476 0.8345
1.500 0.5115 0.00620 0.00177 -0.0807 0.7357 0.8654
1.750 0.5413 0.00612 0.00182 -0.0809 0.7221 0.9332
2.000 0.5833 0.00619 0.00182 -0.0840 0.7009 1.0000
2.250 0.6089 0.00632 0.00186 -0.0836 0.6810 1.0000
2.500 0.6345 0.00645 0.00193 -0.0832 0.6587 1.0000
2.750 0.6597 0.00662 0.00201 -0.0827 0.6344 1.0000
3.000 0.6846 0.00681 0.00210 -0.0822 0.6097 1.0000
3.250 0.7091 0.00704 0.00222 -0.0816 0.5790 1.0000
3.500 0.7327 0.00735 0.00239 -0.0808 0.5399 1.0000
3.750 0.7544 0.00780 0.00259 -0.0797 0.4799 1.0000
4.000 0.7673 0.00906 0.00308 -0.0774 0.3226 1.0000
4.250 0.7809 0.01047 0.00374 -0.0754 0.1690 1.0000
4.500 0.8025 0.01110 0.00415 -0.0746 0.1287 1.0000
4.750 0.8265 0.01150 0.00449 -0.0741 0.1146 1.0000
5.000 0.8509 0.01185 0.00481 -0.0736 0.0972 1.0000
5.250 0.8717 0.01257 0.00527 -0.0726 0.0491 1.0000
5.500 0.8931 0.01323 0.00595 -0.0716 0.0372 1.0000
5.750 0.9144 0.01391 0.00664 -0.0705 0.0300 1.0000
6.000 0.9361 0.01452 0.00730 -0.0695 0.0270 1.0000
6.250 0.9580 0.01508 0.00790 -0.0686 0.0248 1.0000
6.500 0.9788 0.01574 0.00859 -0.0675 0.0231 1.0000
6.750 0.9935 0.01701 0.00994 -0.0654 0.0213 1.0000
7.000 1.0135 0.01776 0.01075 -0.0642 0.0205 1.0000
7.250 1.0334 0.01854 0.01160 -0.0630 0.0197 1.0000
7.500 1.0526 0.01946 0.01259 -0.0617 0.0191 1.0000
7.750 1.0719 0.02046 0.01365 -0.0604 0.0184 1.0000
8.000 1.0917 0.02152 0.01480 -0.0592 0.0179 1.0000
8.250 1.1119 0.02266 0.01601 -0.0581 0.0173 1.0000
8.500 1.1322 0.02380 0.01722 -0.0571 0.0168 1.0000
8.750 1.1521 0.02515 0.01862 -0.0562 0.0160 1.0000
9.000 1.1748 0.02910 0.02278 -0.0559 0.0153 1.0000
9.250 1.1928 0.03102 0.02493 -0.0545 0.0151 1.0000
9.500 1.2090 0.03287 0.02704 -0.0529 0.0149 1.0000
9.750 1.2224 0.03527 0.02973 -0.0510 0.0148 1.0000
10.000 1.2316 0.03824 0.03301 -0.0487 0.0147 1.0000
10.250 1.2367 0.04121 0.03629 -0.0459 0.0146 1.0000
10.500 1.2375 0.04410 0.03950 -0.0426 0.0143 1.0000
10.750 1.2319 0.04714 0.04284 -0.0388 0.0141 1.0000
11.000 1.2192 0.05053 0.04650 -0.0345 0.0142 1.0000
11.250 1.2013 0.05428 0.05049 -0.0304 0.0144 1.0000
11.500 1.1803 0.05845 0.05489 -0.0272 0.0146 1.0000
11.750 1.0804 0.05237 0.04904 -0.0141 0.0163 1.0000
12.000 1.0656 0.05592 0.05269 -0.0124 0.0161 1.0000
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Polar data table (+)
Polar graphs
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