NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 500,000 Max Cl/Cd: 97.84 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65410-il-500000.txt Download as CSV file: xf-naca65410-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4435 0.09342 0.09111 -0.0427 1.0000 0.0168
-9.750 -0.4428 0.09010 0.08781 -0.0432 1.0000 0.0170
-9.500 -0.4429 0.08650 0.08423 -0.0445 1.0000 0.0171
-9.250 -0.4432 0.08326 0.08102 -0.0453 1.0000 0.0174
-9.000 -0.4457 0.07969 0.07748 -0.0465 1.0000 0.0175
-8.750 -0.4518 0.07588 0.07372 -0.0479 1.0000 0.0177
-8.500 -0.4695 0.07146 0.06937 -0.0498 1.0000 0.0176
-8.250 -0.4973 0.06720 0.06513 -0.0516 0.9983 0.0174
-8.000 -0.4807 0.06106 0.05887 -0.0599 0.9930 0.0177
-7.750 -0.4634 0.05580 0.05347 -0.0661 0.9874 0.0182
-7.500 -0.4415 0.05057 0.04806 -0.0719 0.9837 0.0190
-7.250 -0.4213 0.04564 0.04289 -0.0757 0.9772 0.0205
-7.000 -0.3866 0.04247 0.03923 -0.0786 0.9733 0.0227
-6.750 -0.3592 0.03812 0.03449 -0.0820 0.9705 0.0228
-6.500 -0.3479 0.02991 0.02587 -0.0841 0.9622 0.0241
-6.250 -0.3193 0.02832 0.02426 -0.0860 0.9582 0.0257
-6.000 -0.2922 0.02650 0.02223 -0.0869 0.9524 0.0281
-5.750 -0.2672 0.02052 0.01545 -0.0857 0.9449 0.0215
-5.500 -0.2406 0.01807 0.01264 -0.0856 0.9387 0.0215
-5.250 -0.2146 0.01655 0.01088 -0.0852 0.9313 0.0220
-5.000 -0.1882 0.01498 0.00905 -0.0850 0.9250 0.0237
-4.750 -0.1635 0.01362 0.00761 -0.0845 0.9173 0.0250
-4.500 -0.1371 0.01280 0.00672 -0.0843 0.9110 0.0260
-4.250 -0.1117 0.01214 0.00600 -0.0839 0.9032 0.0274
-4.000 -0.0852 0.01166 0.00545 -0.0836 0.8967 0.0296
-3.750 -0.0592 0.01122 0.00494 -0.0833 0.8889 0.0311
-3.500 -0.0330 0.01068 0.00432 -0.0830 0.8825 0.0323
-3.250 -0.0078 0.00986 0.00344 -0.0828 0.8749 0.0355
-3.000 0.0194 0.00955 0.00309 -0.0828 0.8688 0.0397
-2.750 0.0464 0.00930 0.00277 -0.0827 0.8613 0.0431
-2.500 0.0740 0.00894 0.00236 -0.0827 0.8553 0.0524
-2.250 0.0995 0.00778 0.00198 -0.0832 0.8479 0.2792
-2.000 0.1244 0.00659 0.00188 -0.0835 0.8420 0.6186
-1.750 0.1515 0.00651 0.00189 -0.0833 0.8350 0.6646
-1.500 0.1785 0.00650 0.00193 -0.0830 0.8289 0.7054
-1.250 0.2049 0.00654 0.00204 -0.0825 0.8224 0.7418
-1.000 0.2320 0.00658 0.00207 -0.0822 0.8161 0.7611
-0.750 0.2591 0.00663 0.00211 -0.0819 0.8102 0.7762
-0.500 0.2863 0.00665 0.00213 -0.0818 0.8036 0.7869
-0.250 0.3143 0.00667 0.00212 -0.0818 0.7982 0.7933
0.000 0.3420 0.00668 0.00213 -0.0818 0.7915 0.8004
0.250 0.3699 0.00671 0.00213 -0.0818 0.7859 0.8071
0.500 0.3975 0.00673 0.00217 -0.0818 0.7797 0.8142
0.750 0.4252 0.00675 0.00220 -0.0818 0.7737 0.8211
1.000 0.4529 0.00680 0.00225 -0.0818 0.7682 0.8284
1.250 0.4803 0.00682 0.00230 -0.0817 0.7619 0.8356
1.500 0.5079 0.00687 0.00235 -0.0817 0.7564 0.8431
1.750 0.5347 0.00688 0.00242 -0.0814 0.7481 0.8505
2.000 0.5611 0.00690 0.00244 -0.0811 0.7368 0.8588
2.250 0.5867 0.00690 0.00246 -0.0805 0.7241 0.8663
2.500 0.6126 0.00692 0.00247 -0.0800 0.7085 0.8751
2.750 0.6364 0.00694 0.00249 -0.0789 0.6870 0.8831
3.000 0.6603 0.00700 0.00251 -0.0780 0.6606 0.8923
3.250 0.6843 0.00709 0.00259 -0.0771 0.6374 0.9019
3.500 0.7064 0.00722 0.00267 -0.0758 0.6034 0.9114
3.750 0.7255 0.00751 0.00278 -0.0739 0.5420 0.9228
4.000 0.7311 0.00875 0.00320 -0.0699 0.3594 0.9387
4.250 0.7326 0.01052 0.00393 -0.0656 0.1381 0.9619
4.500 0.7552 0.01166 0.00459 -0.0653 0.0452 1.0000
4.750 0.7817 0.01216 0.00511 -0.0655 0.0373 1.0000
5.000 0.8044 0.01302 0.00601 -0.0649 0.0313 1.0000
5.250 0.8303 0.01343 0.00646 -0.0648 0.0290 1.0000
5.500 0.8543 0.01400 0.00706 -0.0644 0.0266 1.0000
5.750 0.8766 0.01471 0.00779 -0.0637 0.0247 1.0000
6.000 0.8946 0.01590 0.00904 -0.0623 0.0232 1.0000
6.250 0.9125 0.01740 0.01063 -0.0608 0.0222 1.0000
6.500 0.9361 0.01813 0.01141 -0.0603 0.0216 1.0000
6.750 0.9598 0.01887 0.01222 -0.0597 0.0206 1.0000
7.000 0.9833 0.01983 0.01324 -0.0592 0.0196 1.0000
7.250 1.0073 0.02101 0.01450 -0.0587 0.0190 1.0000
7.500 1.0318 0.02234 0.01593 -0.0584 0.0184 1.0000
7.750 1.0562 0.02378 0.01747 -0.0580 0.0178 1.0000
8.000 1.0798 0.02533 0.01914 -0.0576 0.0173 1.0000
8.250 1.1020 0.02728 0.02118 -0.0572 0.0164 1.0000
8.500 1.1203 0.03266 0.02697 -0.0563 0.0159 1.0000
8.750 1.1355 0.03597 0.03059 -0.0548 0.0159 1.0000
9.000 1.1498 0.03862 0.03352 -0.0531 0.0160 1.0000
9.250 1.1634 0.04083 0.03598 -0.0513 0.0161 1.0000
9.500 1.0633 0.05164 0.04820 -0.0388 0.0223 1.0000
9.750 1.0524 0.05559 0.05237 -0.0355 0.0223 1.0000
10.000 1.0341 0.05875 0.05570 -0.0314 0.0223 1.0000
10.250 1.0126 0.06211 0.05922 -0.0280 0.0223 1.0000
10.500 0.9891 0.06592 0.06319 -0.0256 0.0222 1.0000
10.750 0.9655 0.07055 0.06796 -0.0244 0.0223 1.0000
11.000 0.9396 0.07589 0.07345 -0.0242 0.0223 1.0000
11.250 0.9150 0.08154 0.07923 -0.0251 0.0223 1.0000
11.500 0.8896 0.08789 0.08570 -0.0271 0.0223 1.0000
11.750 0.8633 0.09473 0.09266 -0.0302 0.0223 1.0000
12.000 0.8371 0.10198 0.10002 -0.0343 0.0223 1.0000
12.250 0.8118 0.10944 0.10758 -0.0393 0.0224 1.0000
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Polar data table (+)
Polar graphs
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