NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 100,000 Max Cl/Cd: 37.76 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264-il-100000.txt Download as CSV file: xf-naca001264-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6733 0.09084 0.08556 -0.0274 1.0000 0.1925
-9.750 -0.8391 0.06381 0.05764 -0.0309 1.0000 0.0999
-9.500 -0.8427 0.05971 0.05343 -0.0284 1.0000 0.0981
-9.250 -0.8531 0.05554 0.04900 -0.0247 1.0000 0.0956
-9.000 -0.8936 0.05031 0.04266 -0.0156 1.0000 0.0885
-8.750 -0.8881 0.04745 0.03950 -0.0124 1.0000 0.0879
-8.500 -0.8824 0.04425 0.03600 -0.0094 1.0000 0.0876
-8.250 -0.8773 0.04208 0.03342 -0.0058 1.0000 0.0881
-8.000 -0.8673 0.03861 0.02979 -0.0036 1.0000 0.0896
-7.750 -0.8531 0.03644 0.02748 -0.0016 1.0000 0.0911
-7.500 -0.8380 0.03445 0.02528 0.0005 1.0000 0.0922
-7.250 -0.8215 0.03264 0.02325 0.0025 1.0000 0.0935
-7.000 -0.8042 0.03112 0.02152 0.0043 1.0000 0.0960
-6.750 -0.7865 0.02977 0.01990 0.0063 1.0000 0.0990
-6.500 -0.7678 0.02857 0.01837 0.0082 1.0000 0.1014
-6.250 -0.7439 0.02666 0.01652 0.0088 1.0000 0.1046
-6.000 -0.7224 0.02552 0.01537 0.0099 1.0000 0.1089
-5.750 -0.7020 0.02465 0.01433 0.0114 1.0000 0.1148
-5.500 -0.6805 0.02340 0.01323 0.0124 1.0000 0.1217
-5.250 -0.6602 0.02254 0.01230 0.0140 1.0000 0.1305
-5.000 -0.6418 0.02149 0.01141 0.0156 1.0000 0.1431
-4.750 -0.6250 0.02052 0.01062 0.0175 1.0000 0.1624
-4.500 -0.6098 0.01952 0.00987 0.0197 1.0000 0.1929
-4.250 -0.5973 0.01823 0.00909 0.0222 1.0000 0.2505
-4.000 -0.5915 0.01631 0.00843 0.0258 1.0000 0.4257
-3.750 -0.5817 0.01541 0.00880 0.0306 1.0000 0.6658
-3.500 -0.5635 0.01574 0.00939 0.0343 1.0000 0.7637
-3.250 -0.5421 0.01639 0.01008 0.0375 1.0000 0.8194
-3.000 -0.5167 0.01718 0.01079 0.0398 1.0000 0.8569
-2.750 -0.4815 0.01807 0.01155 0.0401 1.0000 0.8840
-2.500 -0.4381 0.01894 0.01225 0.0384 1.0000 0.9068
-2.250 -0.3551 0.02029 0.01336 0.0294 1.0000 0.9275
-2.000 -0.2713 0.02105 0.01392 0.0194 1.0000 0.9440
-1.750 -0.1870 0.02143 0.01414 0.0088 1.0000 0.9615
-1.500 -0.1117 0.02139 0.01399 -0.0008 1.0000 0.9781
-1.250 -0.0605 0.02110 0.01363 -0.0065 1.0000 0.9884
-1.000 -0.0097 0.02078 0.01326 -0.0122 1.0000 0.9978
-0.750 0.0035 0.02062 0.01310 -0.0111 1.0000 1.0000
-0.500 0.0026 0.02056 0.01303 -0.0075 1.0000 1.0000
-0.250 0.0014 0.02052 0.01299 -0.0038 1.0000 1.0000
0.000 0.0000 0.02051 0.01298 0.0000 1.0000 1.0000
0.250 -0.0014 0.02052 0.01299 0.0038 1.0000 1.0000
0.500 -0.0026 0.02056 0.01303 0.0075 1.0000 1.0000
0.750 -0.0035 0.02062 0.01309 0.0111 1.0000 1.0000
1.000 0.0096 0.02077 0.01325 0.0122 0.9978 1.0000
1.250 0.0605 0.02110 0.01362 0.0065 0.9885 1.0000
1.500 0.1116 0.02138 0.01398 0.0008 0.9781 1.0000
1.750 0.1868 0.02142 0.01413 -0.0087 0.9616 1.0000
2.000 0.2712 0.02104 0.01391 -0.0193 0.9440 1.0000
2.250 0.3549 0.02028 0.01335 -0.0294 0.9275 1.0000
2.500 0.4382 0.01894 0.01224 -0.0384 0.9069 1.0000
2.750 0.4814 0.01807 0.01154 -0.0401 0.8841 1.0000
3.000 0.5166 0.01718 0.01078 -0.0398 0.8569 1.0000
3.250 0.5419 0.01639 0.01008 -0.0375 0.8194 1.0000
3.500 0.5634 0.01573 0.00939 -0.0343 0.7639 1.0000
3.750 0.5815 0.01540 0.00880 -0.0306 0.6660 1.0000
4.000 0.5914 0.01631 0.00843 -0.0257 0.4261 1.0000
4.250 0.5972 0.01823 0.00909 -0.0222 0.2507 1.0000
4.500 0.6097 0.01951 0.00986 -0.0197 0.1930 1.0000
4.750 0.6249 0.02052 0.01062 -0.0175 0.1624 1.0000
5.000 0.6417 0.02149 0.01141 -0.0156 0.1431 1.0000
5.250 0.6601 0.02254 0.01229 -0.0140 0.1305 1.0000
5.500 0.6804 0.02339 0.01323 -0.0124 0.1217 1.0000
5.750 0.7019 0.02464 0.01432 -0.0114 0.1148 1.0000
6.000 0.7223 0.02552 0.01536 -0.0099 0.1089 1.0000
6.250 0.7438 0.02666 0.01651 -0.0087 0.1046 1.0000
6.500 0.7677 0.02856 0.01837 -0.0082 0.1014 1.0000
6.750 0.7864 0.02977 0.01989 -0.0063 0.0990 1.0000
7.000 0.8041 0.03112 0.02151 -0.0043 0.0960 1.0000
7.250 0.8214 0.03264 0.02324 -0.0025 0.0935 1.0000
7.500 0.8379 0.03445 0.02528 -0.0005 0.0922 1.0000
7.750 0.8531 0.03644 0.02748 0.0016 0.0911 1.0000
8.000 0.8672 0.03861 0.02978 0.0036 0.0896 1.0000
8.250 0.8773 0.04207 0.03341 0.0058 0.0881 1.0000
8.500 0.8823 0.04425 0.03600 0.0094 0.0876 1.0000
8.750 0.8881 0.04745 0.03950 0.0124 0.0879 1.0000
9.000 0.8935 0.05030 0.04266 0.0156 0.0885 1.0000
9.250 0.8531 0.05555 0.04900 0.0247 0.0956 1.0000
9.500 0.8428 0.05972 0.05343 0.0284 0.0981 1.0000
9.750 0.8393 0.06383 0.05765 0.0308 0.0999 1.0000
10.000 0.7009 0.06196 0.05652 0.0429 0.1139 1.0000
10.250 0.6054 0.09996 0.09449 0.0172 0.1825 1.0000
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Polar data table (+)
Polar graphs
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