NACA 0010 (naca0010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 100,000 Max Cl/Cd: 35.83 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0010-il-100000.txt Download as CSV file: xf-naca0010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5558 0.10754 0.10264 -0.0010 1.0000 0.1703
-10.250 -0.5343 0.10341 0.09848 0.0011 1.0000 0.1742
-10.000 -0.8387 0.07240 0.06713 -0.0217 1.0000 0.0863
-9.750 -0.8376 0.06731 0.06193 -0.0216 1.0000 0.0833
-9.500 -0.8461 0.06193 0.05638 -0.0213 1.0000 0.0816
-9.250 -0.8578 0.05611 0.05023 -0.0205 1.0000 0.0796
-9.000 -0.8653 0.05042 0.04406 -0.0191 1.0000 0.0779
-8.750 -0.8624 0.04631 0.03952 -0.0175 1.0000 0.0790
-8.500 -0.8555 0.04268 0.03542 -0.0158 1.0000 0.0810
-8.250 -0.8453 0.03918 0.03137 -0.0140 1.0000 0.0824
-8.000 -0.8315 0.03632 0.02792 -0.0121 1.0000 0.0842
-7.750 -0.8149 0.03338 0.02466 -0.0110 1.0000 0.0875
-7.500 -0.7938 0.03141 0.02257 -0.0101 1.0000 0.0909
-7.250 -0.7723 0.02952 0.02040 -0.0090 1.0000 0.0944
-7.000 -0.7507 0.02814 0.01856 -0.0077 1.0000 0.0987
-6.750 -0.7269 0.02595 0.01640 -0.0072 1.0000 0.1027
-6.500 -0.7028 0.02452 0.01487 -0.0064 1.0000 0.1073
-6.250 -0.6789 0.02328 0.01342 -0.0054 1.0000 0.1137
-6.000 -0.6557 0.02196 0.01224 -0.0046 1.0000 0.1219
-5.750 -0.6326 0.02066 0.01097 -0.0036 1.0000 0.1312
-5.500 -0.6109 0.01945 0.00988 -0.0024 1.0000 0.1459
-5.250 -0.5910 0.01823 0.00885 -0.0009 1.0000 0.1732
-5.000 -0.5732 0.01696 0.00799 0.0007 1.0000 0.2248
-4.750 -0.5559 0.01583 0.00735 0.0024 1.0000 0.2991
-4.500 -0.5374 0.01504 0.00693 0.0041 1.0000 0.3732
-4.250 -0.5181 0.01446 0.00663 0.0058 1.0000 0.4430
-4.000 -0.4990 0.01399 0.00647 0.0077 1.0000 0.5103
-3.750 -0.4795 0.01362 0.00637 0.0098 1.0000 0.5737
-3.500 -0.4591 0.01333 0.00628 0.0118 1.0000 0.6288
-3.250 -0.4382 0.01310 0.00620 0.0139 1.0000 0.6780
-3.000 -0.4174 0.01294 0.00619 0.0161 1.0000 0.7254
-2.750 -0.3966 0.01288 0.00623 0.0185 1.0000 0.7710
-2.500 -0.3752 0.01291 0.00633 0.0210 1.0000 0.8146
-2.250 -0.3522 0.01302 0.00647 0.0232 1.0000 0.8560
-2.000 -0.3203 0.01327 0.00669 0.0237 1.0000 0.8918
-1.750 -0.2755 0.01358 0.00690 0.0214 1.0000 0.9233
-1.500 -0.2169 0.01387 0.00705 0.0160 1.0000 0.9486
-1.250 -0.1443 0.01402 0.00705 0.0073 1.0000 0.9659
-1.000 -0.0760 0.01395 0.00688 -0.0009 1.0000 0.9830
-0.750 -0.0075 0.01371 0.00657 -0.0096 1.0000 0.9974
-0.500 0.0072 0.01343 0.00629 -0.0087 1.0000 1.0000
-0.250 0.0055 0.01326 0.00614 -0.0047 1.0000 1.0000
0.000 0.0000 0.01320 0.00609 0.0000 1.0000 1.0000
0.250 -0.0055 0.01326 0.00614 0.0047 1.0000 1.0000
0.500 -0.0072 0.01343 0.00629 0.0087 1.0000 1.0000
0.750 0.0075 0.01371 0.00656 0.0096 0.9974 1.0000
1.000 0.0760 0.01395 0.00688 0.0009 0.9830 1.0000
1.250 0.1442 0.01401 0.00705 -0.0073 0.9659 1.0000
1.500 0.2168 0.01387 0.00705 -0.0160 0.9486 1.0000
1.750 0.2754 0.01358 0.00690 -0.0214 0.9233 1.0000
2.000 0.3203 0.01327 0.00669 -0.0237 0.8918 1.0000
2.250 0.3522 0.01302 0.00647 -0.0232 0.8560 1.0000
2.500 0.3752 0.01291 0.00633 -0.0210 0.8146 1.0000
2.750 0.3965 0.01287 0.00623 -0.0185 0.7710 1.0000
3.000 0.4174 0.01294 0.00619 -0.0161 0.7254 1.0000
3.250 0.4382 0.01310 0.00620 -0.0139 0.6780 1.0000
3.500 0.4591 0.01333 0.00627 -0.0118 0.6288 1.0000
3.750 0.4795 0.01362 0.00637 -0.0098 0.5737 1.0000
4.000 0.4990 0.01399 0.00647 -0.0077 0.5103 1.0000
4.250 0.5181 0.01446 0.00663 -0.0058 0.4430 1.0000
4.500 0.5374 0.01504 0.00693 -0.0041 0.3732 1.0000
4.750 0.5558 0.01583 0.00735 -0.0024 0.2991 1.0000
5.000 0.5732 0.01696 0.00799 -0.0007 0.2248 1.0000
5.250 0.5910 0.01823 0.00885 0.0009 0.1732 1.0000
5.500 0.6109 0.01945 0.00988 0.0024 0.1460 1.0000
5.750 0.6326 0.02066 0.01097 0.0036 0.1313 1.0000
6.000 0.6557 0.02196 0.01224 0.0046 0.1219 1.0000
6.250 0.6789 0.02328 0.01342 0.0054 0.1137 1.0000
6.500 0.7028 0.02452 0.01487 0.0064 0.1073 1.0000
6.750 0.7269 0.02595 0.01640 0.0072 0.1027 1.0000
7.000 0.7507 0.02814 0.01856 0.0077 0.0987 1.0000
7.250 0.7723 0.02953 0.02040 0.0090 0.0944 1.0000
7.500 0.7938 0.03141 0.02257 0.0101 0.0909 1.0000
7.750 0.8149 0.03338 0.02466 0.0110 0.0875 1.0000
8.000 0.8316 0.03633 0.02792 0.0121 0.0842 1.0000
8.250 0.8453 0.03919 0.03137 0.0140 0.0824 1.0000
8.500 0.8555 0.04269 0.03542 0.0158 0.0810 1.0000
8.750 0.8625 0.04631 0.03952 0.0175 0.0790 1.0000
9.000 0.8654 0.05042 0.04407 0.0190 0.0779 1.0000
9.250 0.8579 0.05613 0.05025 0.0205 0.0796 1.0000
9.500 0.8462 0.06195 0.05640 0.0213 0.0817 1.0000
9.750 0.8378 0.06733 0.06195 0.0216 0.0834 1.0000
10.000 0.8396 0.07272 0.06737 0.0216 0.0846 1.0000
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Polar data table (+)
Polar graphs
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