NACA 1410 (naca1410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 50,000 Max Cl/Cd: 31.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1410-il-50000-n5.txt Download as CSV file: xf-naca1410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6451 0.09163 0.08427 -0.0199 1.0000 0.0655
-10.000 -0.6606 0.08314 0.07580 -0.0264 1.0000 0.0652
-9.750 -0.6812 0.07590 0.06859 -0.0317 1.0000 0.0647
-9.500 -0.7025 0.07015 0.06275 -0.0339 1.0000 0.0645
-9.250 -0.7196 0.06458 0.05697 -0.0353 1.0000 0.0646
-9.000 -0.7316 0.05934 0.05140 -0.0357 1.0000 0.0651
-8.750 -0.7376 0.05443 0.04604 -0.0353 1.0000 0.0658
-8.500 -0.7383 0.04990 0.04093 -0.0344 1.0000 0.0667
-8.250 -0.7258 0.04739 0.03834 -0.0336 1.0000 0.0693
-8.000 -0.7121 0.04521 0.03600 -0.0327 1.0000 0.0725
-7.750 -0.6999 0.04224 0.03261 -0.0315 1.0000 0.0753
-7.500 -0.6857 0.03921 0.02906 -0.0303 1.0000 0.0775
-7.250 -0.6690 0.03677 0.02620 -0.0292 1.0000 0.0811
-7.000 -0.6498 0.03519 0.02457 -0.0283 1.0000 0.0853
-6.750 -0.6297 0.03328 0.02235 -0.0272 1.0000 0.0892
-6.500 -0.6080 0.03139 0.02003 -0.0261 1.0000 0.0928
-6.250 -0.5868 0.02991 0.01856 -0.0251 1.0000 0.0974
-6.000 -0.5654 0.02870 0.01719 -0.0241 1.0000 0.1048
-5.750 -0.5436 0.02743 0.01586 -0.0230 1.0000 0.1116
-5.500 -0.5214 0.02625 0.01455 -0.0219 1.0000 0.1197
-5.250 -0.5001 0.02515 0.01347 -0.0207 1.0000 0.1299
-5.000 -0.4788 0.02418 0.01251 -0.0197 1.0000 0.1466
-4.750 -0.4575 0.02322 0.01161 -0.0187 1.0000 0.1684
-4.500 -0.4362 0.02231 0.01082 -0.0178 1.0000 0.1991
-4.250 -0.4149 0.02147 0.01016 -0.0169 1.0000 0.2419
-4.000 -0.3946 0.02063 0.00955 -0.0159 1.0000 0.2941
-3.750 -0.3754 0.01977 0.00906 -0.0146 1.0000 0.3540
-3.500 -0.3568 0.01910 0.00880 -0.0129 1.0000 0.4298
-3.250 -0.3376 0.01862 0.00855 -0.0111 1.0000 0.5113
-3.000 -0.3189 0.01816 0.00839 -0.0089 1.0000 0.5839
-2.750 -0.3003 0.01783 0.00833 -0.0063 1.0000 0.6568
-2.500 -0.2808 0.01761 0.00830 -0.0037 1.0000 0.7274
-2.250 -0.2576 0.01751 0.00832 -0.0017 1.0000 0.7961
-2.000 -0.2245 0.01754 0.00834 -0.0017 1.0000 0.8637
-1.750 -0.1767 0.01763 0.00829 -0.0050 1.0000 0.9258
-1.500 -0.1181 0.01769 0.00814 -0.0112 1.0000 0.9763
-1.250 -0.0780 0.01762 0.00789 -0.0147 1.0000 1.0000
-1.000 -0.0726 0.01759 0.00775 -0.0118 1.0000 1.0000
-0.750 -0.0637 0.01765 0.00769 -0.0094 1.0000 1.0000
-0.500 -0.0521 0.01779 0.00771 -0.0075 1.0000 1.0000
-0.250 -0.0148 0.01801 0.00782 -0.0103 0.9905 1.0000
0.000 0.0309 0.01824 0.00796 -0.0146 0.9768 1.0000
0.250 0.0762 0.01844 0.00809 -0.0187 0.9627 1.0000
0.500 0.1209 0.01859 0.00822 -0.0225 0.9480 1.0000
0.750 0.1653 0.01871 0.00833 -0.0261 0.9327 1.0000
1.000 0.2088 0.01879 0.00843 -0.0293 0.9169 1.0000
1.250 0.2477 0.01883 0.00851 -0.0314 0.8990 1.0000
1.500 0.2836 0.01887 0.00859 -0.0329 0.8795 1.0000
1.750 0.3196 0.01887 0.00865 -0.0341 0.8599 1.0000
2.000 0.3543 0.01885 0.00868 -0.0349 0.8397 1.0000
2.250 0.3841 0.01888 0.00875 -0.0348 0.8163 1.0000
2.500 0.4150 0.01887 0.00880 -0.0346 0.7939 1.0000
2.750 0.4422 0.01893 0.00890 -0.0338 0.7688 1.0000
3.000 0.4690 0.01900 0.00902 -0.0329 0.7434 1.0000
3.250 0.4956 0.01908 0.00910 -0.0318 0.7174 1.0000
3.500 0.5203 0.01921 0.00925 -0.0304 0.6889 1.0000
3.750 0.5443 0.01938 0.00943 -0.0289 0.6589 1.0000
4.000 0.5678 0.01958 0.00962 -0.0274 0.6275 1.0000
4.250 0.5909 0.01984 0.00985 -0.0258 0.5939 1.0000
4.500 0.6131 0.02014 0.01012 -0.0241 0.5568 1.0000
4.750 0.6346 0.02048 0.01040 -0.0224 0.5168 1.0000
5.000 0.6552 0.02089 0.01072 -0.0206 0.4735 1.0000
5.250 0.6750 0.02139 0.01111 -0.0188 0.4263 1.0000
5.500 0.6935 0.02200 0.01159 -0.0170 0.3716 1.0000
5.750 0.7106 0.02280 0.01211 -0.0152 0.3095 1.0000
6.000 0.7271 0.02385 0.01282 -0.0136 0.2484 1.0000
6.250 0.7442 0.02509 0.01377 -0.0123 0.1991 1.0000
6.500 0.7620 0.02644 0.01493 -0.0111 0.1640 1.0000
6.750 0.7797 0.02784 0.01620 -0.0099 0.1403 1.0000
7.000 0.7985 0.02919 0.01753 -0.0087 0.1233 1.0000
7.250 0.8177 0.03062 0.01891 -0.0075 0.1132 1.0000
7.500 0.8393 0.03204 0.02049 -0.0064 0.1050 1.0000
7.750 0.8603 0.03356 0.02206 -0.0055 0.0984 1.0000
8.000 0.8815 0.03504 0.02373 -0.0046 0.0913 1.0000
8.250 0.9028 0.03676 0.02537 -0.0039 0.0867 1.0000
8.500 0.9253 0.03881 0.02782 -0.0030 0.0831 1.0000
8.750 0.9449 0.04091 0.03021 -0.0020 0.0792 1.0000
9.000 0.9629 0.04277 0.03214 -0.0012 0.0751 1.0000
9.250 0.9781 0.04531 0.03502 0.0000 0.0720 1.0000
9.500 0.9895 0.04835 0.03856 0.0014 0.0698 1.0000
9.750 0.9975 0.05133 0.04195 0.0029 0.0673 1.0000
10.000 1.0050 0.05392 0.04478 0.0043 0.0645 1.0000
10.250 1.0146 0.05634 0.04726 0.0053 0.0621 1.0000
10.500 1.0136 0.05996 0.05116 0.0068 0.0609 1.0000
10.750 1.0017 0.06402 0.05565 0.0086 0.0604 1.0000
11.000 0.9833 0.06805 0.05999 0.0104 0.0601 1.0000
11.250 0.9614 0.07258 0.06477 0.0109 0.0600 1.0000
11.500 0.9374 0.07798 0.07037 0.0096 0.0601 1.0000
11.750 0.9122 0.08451 0.07705 0.0063 0.0603 1.0000
12.000 0.8867 0.09228 0.08493 0.0014 0.0607 1.0000
12.250 0.8625 0.10114 0.09384 -0.0044 0.0611 1.0000
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Polar data table (+)
Polar graphs
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