NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 500,000 Max Cl/Cd: 37.36 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca000834-il-500000-n5.txt Download as CSV file: xf-naca000834-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6428 0.10064 0.09845 0.0011 1.0000 0.0056
-9.500 -0.6442 0.09558 0.09341 -0.0018 1.0000 0.0057
-9.250 -0.6465 0.09024 0.08809 -0.0052 1.0000 0.0057
-7.250 -0.6256 0.03586 0.03320 -0.0226 1.0000 0.0057
-6.750 -0.6579 0.04119 0.03780 -0.0144 1.0000 0.0045
-6.500 -0.6539 0.03783 0.03421 -0.0118 1.0000 0.0041
-6.250 -0.6460 0.03441 0.03052 -0.0087 1.0000 0.0038
-6.000 -0.6368 0.03073 0.02648 -0.0053 1.0000 0.0034
-5.750 -0.6272 0.02521 0.02045 -0.0004 1.0000 0.0029
-5.500 -0.6120 0.02164 0.01642 0.0028 0.9999 0.0028
-5.250 -0.5846 0.01872 0.01307 0.0031 0.9982 0.0029
-5.000 -0.5557 0.01689 0.01096 0.0027 0.9964 0.0031
-4.750 -0.5261 0.01543 0.00929 0.0023 0.9949 0.0034
-4.500 -0.4973 0.01420 0.00790 0.0020 0.9926 0.0040
-4.250 -0.4676 0.01326 0.00681 0.0015 0.9903 0.0050
-4.000 -0.4386 0.01210 0.00553 0.0010 0.9882 0.0054
-3.750 -0.4088 0.01133 0.00467 0.0003 0.9858 0.0060
-3.500 -0.3794 0.01071 0.00397 -0.0002 0.9826 0.0071
-3.250 -0.3481 0.01014 0.00329 -0.0011 0.9800 0.0098
-3.000 -0.3155 0.00973 0.00278 -0.0023 0.9780 0.0143
-2.750 -0.2872 0.00927 0.00242 -0.0027 0.9735 0.0479
-2.500 -0.2622 0.00798 0.00200 -0.0030 0.9691 0.2754
-2.250 -0.2419 0.00659 0.00170 -0.0024 0.9635 0.5538
-2.000 -0.2197 0.00588 0.00160 -0.0013 0.9572 0.7123
-1.750 -0.1925 0.00565 0.00154 -0.0010 0.9519 0.7702
-1.500 -0.1652 0.00554 0.00147 -0.0009 0.9447 0.7971
-1.250 -0.1367 0.00546 0.00139 -0.0010 0.9381 0.8193
-1.000 -0.1093 0.00539 0.00135 -0.0008 0.9296 0.8385
-0.750 -0.0820 0.00535 0.00131 -0.0006 0.9206 0.8542
-0.500 -0.0544 0.00532 0.00128 -0.0004 0.9117 0.8678
-0.250 -0.0272 0.00530 0.00126 -0.0002 0.9017 0.8799
0.000 0.0000 0.00529 0.00126 0.0000 0.8911 0.8911
0.250 0.0272 0.00530 0.00126 0.0002 0.8799 0.9016
0.500 0.0544 0.00532 0.00128 0.0004 0.8677 0.9116
0.750 0.0820 0.00535 0.00131 0.0006 0.8541 0.9206
1.000 0.1093 0.00539 0.00135 0.0008 0.8385 0.9296
1.250 0.1366 0.00546 0.00139 0.0010 0.8193 0.9381
1.500 0.1651 0.00554 0.00147 0.0009 0.7970 0.9447
1.750 0.1924 0.00565 0.00154 0.0011 0.7694 0.9520
2.000 0.2197 0.00588 0.00160 0.0013 0.7122 0.9573
2.250 0.2417 0.00659 0.00170 0.0024 0.5527 0.9636
2.500 0.2623 0.00797 0.00199 0.0030 0.2773 0.9691
2.750 0.2872 0.00927 0.00242 0.0027 0.0475 0.9735
3.000 0.3157 0.00973 0.00277 0.0023 0.0142 0.9780
3.250 0.3483 0.01014 0.00328 0.0011 0.0099 0.9801
3.500 0.3794 0.01071 0.00396 0.0002 0.0071 0.9826
3.750 0.4088 0.01133 0.00467 -0.0003 0.0060 0.9860
4.000 0.4389 0.01210 0.00553 -0.0010 0.0054 0.9883
4.250 0.4679 0.01326 0.00681 -0.0015 0.0050 0.9905
4.500 0.4975 0.01420 0.00789 -0.0021 0.0040 0.9928
4.750 0.5262 0.01542 0.00929 -0.0023 0.0034 0.9951
5.000 0.5560 0.01689 0.01096 -0.0028 0.0031 0.9966
5.250 0.5849 0.01874 0.01309 -0.0031 0.0029 0.9983
5.500 0.6118 0.02162 0.01639 -0.0028 0.0028 1.0000
5.750 0.6267 0.02517 0.02040 0.0005 0.0029 1.0000
6.000 0.6365 0.03071 0.02646 0.0053 0.0034 1.0000
6.250 0.6458 0.03439 0.03049 0.0088 0.0038 1.0000
6.500 0.6538 0.03782 0.03419 0.0118 0.0041 1.0000
6.750 0.6556 0.04128 0.03788 0.0143 0.0046 1.0000
10.000 0.6431 0.10557 0.10336 -0.0038 0.0056 1.0000
10.250 0.6430 0.11028 0.10806 -0.0061 0.0056 1.0000
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Polar data table (+)
Polar graphs
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