NACA 0008 (naca0008-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.34 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0008-il-1000000.txt Download as CSV file: xf-naca0008-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.0247 0.00392 0.00087 0.0010 0.8212 0.8829
0.500 0.0494 0.00400 0.00089 0.0021 0.7823 0.9085
0.750 0.0738 0.00416 0.00091 0.0031 0.7296 0.9305
1.000 0.0983 0.00443 0.00094 0.0041 0.6563 0.9493
1.250 0.1252 0.00472 0.00099 0.0044 0.5857 0.9636
1.500 0.1551 0.00495 0.00105 0.0041 0.5339 0.9743
1.750 0.1880 0.00519 0.00111 0.0029 0.4833 0.9809
2.000 0.2208 0.00548 0.00120 0.0018 0.4244 0.9867
2.250 0.2567 0.00584 0.00129 -0.0002 0.3520 0.9897
2.500 0.2913 0.00619 0.00141 -0.0019 0.2893 0.9934
2.750 0.3264 0.00657 0.00154 -0.0037 0.2253 0.9959
3.000 0.3616 0.00696 0.00169 -0.0056 0.1636 0.9982
3.250 0.3954 0.00740 0.00188 -0.0072 0.1049 1.0000
3.500 0.4193 0.00780 0.00208 -0.0065 0.0606 1.0000
3.750 0.4436 0.00808 0.00228 -0.0058 0.0467 1.0000
4.000 0.4681 0.00830 0.00251 -0.0051 0.0422 1.0000
4.250 0.4927 0.00850 0.00273 -0.0045 0.0397 1.0000
4.500 0.5173 0.00874 0.00298 -0.0038 0.0373 1.0000
4.750 0.5417 0.00905 0.00331 -0.0031 0.0349 1.0000
5.000 0.5655 0.00953 0.00386 -0.0023 0.0327 1.0000
5.250 0.5909 0.00964 0.00398 -0.0018 0.0321 1.0000
5.500 0.6162 0.00980 0.00416 -0.0013 0.0309 1.0000
5.750 0.6417 0.00997 0.00434 -0.0008 0.0288 1.0000
6.000 0.6671 0.01019 0.00454 -0.0004 0.0261 1.0000
6.250 0.6915 0.01067 0.00507 0.0002 0.0228 1.0000
6.500 0.7181 0.01071 0.00512 0.0005 0.0209 1.0000
6.750 0.7442 0.01089 0.00525 0.0008 0.0176 1.0000
7.000 0.7687 0.01148 0.00588 0.0014 0.0146 1.0000
7.250 0.7944 0.01178 0.00621 0.0017 0.0133 1.0000
7.500 0.8198 0.01215 0.00658 0.0021 0.0120 1.0000
7.750 0.8430 0.01300 0.00753 0.0028 0.0104 1.0000
8.000 0.8664 0.01380 0.00846 0.0035 0.0098 1.0000
8.250 0.8914 0.01426 0.00898 0.0039 0.0093 1.0000
8.500 0.9160 0.01477 0.00954 0.0043 0.0087 1.0000
8.750 0.9403 0.01534 0.01017 0.0048 0.0081 1.0000
9.000 0.9638 0.01603 0.01093 0.0053 0.0077 1.0000
9.250 0.9839 0.01740 0.01245 0.0063 0.0072 1.0000
9.500 1.0010 0.01935 0.01467 0.0075 0.0068 1.0000
9.750 1.0232 0.02023 0.01567 0.0082 0.0066 1.0000
10.000 1.0439 0.02132 0.01695 0.0089 0.0065 1.0000
10.250 1.0634 0.02259 0.01839 0.0098 0.0063 1.0000
10.500 1.0815 0.02402 0.01999 0.0107 0.0061 1.0000
10.750 1.0982 0.02556 0.02173 0.0117 0.0059 1.0000
11.000 1.1135 0.02721 0.02356 0.0127 0.0057 1.0000
11.250 1.1283 0.02877 0.02529 0.0137 0.0055 1.0000
11.500 1.1427 0.03020 0.02686 0.0146 0.0053 1.0000
11.750 1.1557 0.03167 0.02844 0.0156 0.0052 1.0000
12.000 1.1635 0.03362 0.03055 0.0167 0.0051 1.0000
12.250 1.1620 0.03627 0.03339 0.0184 0.0049 1.0000
12.500 1.1476 0.03960 0.03694 0.0204 0.0049 1.0000
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Polar data table (+)
Polar graphs
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