NACA 0006 (naca0006-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0006 (naca0006-il) Reynolds number: 200,000 Max Cl/Cd: 38.91 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0006-il-200000.txt Download as CSV file: xf-naca0006-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0006
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5830 0.09692 0.09373 0.0063 1.0000 0.0398
-9.250 -0.5886 0.09183 0.08866 0.0035 1.0000 0.0399
-7.750 -0.7058 0.07163 0.06793 -0.0079 1.0000 0.0399
-7.500 -0.7044 0.06601 0.06208 -0.0097 1.0000 0.0402
-7.250 -0.7011 0.05867 0.05482 -0.0104 1.0000 0.0416
-7.000 -0.6897 0.05497 0.05108 -0.0105 1.0000 0.0429
-6.750 -0.6770 0.05117 0.04713 -0.0109 1.0000 0.0448
-6.500 -0.6625 0.04700 0.04268 -0.0113 1.0000 0.0477
-6.250 -0.6495 0.04211 0.03710 -0.0114 1.0000 0.0537
-6.000 -0.6311 0.03928 0.03438 -0.0113 1.0000 0.0580
-5.750 -0.6072 0.03004 0.02356 -0.0080 1.0000 0.0304
-5.500 -0.5857 0.02563 0.01880 -0.0071 1.0000 0.0288
-5.250 -0.5617 0.02263 0.01532 -0.0060 1.0000 0.0289
-5.000 -0.5364 0.02054 0.01275 -0.0049 1.0000 0.0304
-4.750 -0.5126 0.01830 0.01046 -0.0044 1.0000 0.0352
-4.500 -0.4866 0.01684 0.00879 -0.0035 1.0000 0.0392
-4.250 -0.4626 0.01521 0.00716 -0.0027 1.0000 0.0482
-4.000 -0.4385 0.01388 0.00581 -0.0019 1.0000 0.0593
-3.750 -0.4140 0.01298 0.00489 -0.0013 1.0000 0.0738
-3.500 -0.3891 0.01226 0.00416 -0.0007 1.0000 0.0888
-3.250 -0.3645 0.01141 0.00343 -0.0001 1.0000 0.1168
-3.000 -0.3466 0.00930 0.00284 0.0008 1.0000 0.4274
-2.750 -0.3265 0.00842 0.00262 0.0024 1.0000 0.5976
-2.500 -0.3060 0.00787 0.00252 0.0045 1.0000 0.7194
-2.250 -0.2850 0.00755 0.00249 0.0068 1.0000 0.8172
-2.000 -0.2572 0.00748 0.00253 0.0080 1.0000 0.9037
-1.750 -0.2082 0.00757 0.00252 0.0044 1.0000 0.9654
-1.500 -0.1297 0.00764 0.00241 -0.0060 1.0000 1.0000
-1.250 -0.1074 0.00752 0.00220 -0.0053 1.0000 1.0000
-1.000 -0.0852 0.00743 0.00205 -0.0045 1.0000 1.0000
-0.750 -0.0633 0.00737 0.00194 -0.0035 1.0000 1.0000
-0.500 -0.0417 0.00732 0.00187 -0.0025 1.0000 1.0000
-0.250 -0.0206 0.00729 0.00181 -0.0013 1.0000 1.0000
0.000 0.0000 0.00728 0.00180 0.0000 1.0000 1.0000
0.250 0.0206 0.00729 0.00181 0.0013 1.0000 1.0000
0.500 0.0417 0.00732 0.00187 0.0025 1.0000 1.0000
0.750 0.0633 0.00736 0.00194 0.0035 1.0000 1.0000
1.000 0.0852 0.00743 0.00205 0.0045 1.0000 1.0000
1.250 0.1074 0.00752 0.00220 0.0053 1.0000 1.0000
1.500 0.1297 0.00764 0.00241 0.0060 1.0000 1.0000
1.750 0.2081 0.00757 0.00252 -0.0044 0.9655 1.0000
2.000 0.2571 0.00748 0.00253 -0.0080 0.9037 1.0000
2.250 0.2849 0.00755 0.00249 -0.0068 0.8174 1.0000
2.500 0.3058 0.00786 0.00252 -0.0045 0.7197 1.0000
2.750 0.3263 0.00842 0.00262 -0.0024 0.5981 1.0000
3.000 0.3465 0.00930 0.00284 -0.0008 0.4282 1.0000
3.250 0.3644 0.01141 0.00343 0.0001 0.1170 1.0000
3.500 0.3890 0.01226 0.00416 0.0007 0.0889 1.0000
3.750 0.4139 0.01298 0.00489 0.0013 0.0738 1.0000
4.000 0.4385 0.01388 0.00581 0.0019 0.0594 1.0000
4.250 0.4625 0.01521 0.00716 0.0028 0.0481 1.0000
4.500 0.4865 0.01684 0.00879 0.0035 0.0392 1.0000
4.750 0.5125 0.01830 0.01046 0.0044 0.0352 1.0000
5.000 0.5364 0.02050 0.01271 0.0049 0.0304 1.0000
5.250 0.5618 0.02263 0.01532 0.0059 0.0289 1.0000
5.500 0.5858 0.02564 0.01881 0.0071 0.0288 1.0000
5.750 0.6072 0.03007 0.02359 0.0080 0.0304 1.0000
6.000 0.6312 0.03926 0.03436 0.0113 0.0579 1.0000
6.250 0.6496 0.04212 0.03711 0.0114 0.0537 1.0000
6.500 0.6626 0.04701 0.04269 0.0113 0.0477 1.0000
6.750 0.6771 0.05118 0.04714 0.0109 0.0448 1.0000
7.000 0.6899 0.05498 0.05109 0.0105 0.0429 1.0000
7.250 0.7012 0.05868 0.05483 0.0104 0.0416 1.0000
7.500 0.7042 0.06619 0.06226 0.0096 0.0402 1.0000
7.750 0.7060 0.07165 0.06795 0.0078 0.0399 1.0000
8.000 0.7075 0.07636 0.07291 0.0047 0.0396 1.0000
8.250 0.7062 0.08309 0.07983 -0.0032 0.0390 1.0000
8.500 0.7028 0.08984 0.08658 -0.0120 0.0385 1.0000
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Polar data table (+)
Polar graphs
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