NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 100,000 Max Cl/Cd: 36.23 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001064-il-100000.txt Download as CSV file: xf-naca001064-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6430 0.09341 0.08824 -0.0111 1.0000 0.1629
-9.250 -0.6758 0.08704 0.08198 -0.0184 1.0000 0.1696
-9.000 -0.7322 0.08233 0.07721 -0.0212 1.0000 0.1710
-8.750 -0.6806 0.07890 0.07388 -0.0181 1.0000 0.1799
-8.500 -0.7583 0.07578 0.07048 -0.0191 1.0000 0.1863
-8.000 -0.7863 0.05471 0.04821 -0.0175 1.0000 0.1143
-7.750 -0.7920 0.04599 0.03834 -0.0123 1.0000 0.0848
-7.500 -0.7817 0.04189 0.03402 -0.0102 1.0000 0.0837
-7.250 -0.7721 0.03918 0.03086 -0.0073 1.0000 0.0843
-7.000 -0.7603 0.03708 0.02826 -0.0044 1.0000 0.0852
-6.750 -0.7452 0.03410 0.02495 -0.0023 1.0000 0.0855
-6.500 -0.7275 0.03121 0.02179 -0.0006 1.0000 0.0865
-6.250 -0.7079 0.02935 0.01988 0.0006 1.0000 0.0899
-6.000 -0.6876 0.02782 0.01817 0.0020 1.0000 0.0930
-5.750 -0.6658 0.02622 0.01631 0.0035 1.0000 0.0952
-5.500 -0.6432 0.02489 0.01471 0.0048 1.0000 0.0980
-5.250 -0.6202 0.02333 0.01320 0.0057 1.0000 0.1030
-5.000 -0.5978 0.02227 0.01208 0.0068 1.0000 0.1085
-4.750 -0.5749 0.02117 0.01090 0.0080 1.0000 0.1141
-4.500 -0.5542 0.02004 0.00994 0.0093 1.0000 0.1225
-4.250 -0.5350 0.01908 0.00909 0.0109 1.0000 0.1364
-4.000 -0.5175 0.01802 0.00821 0.0129 1.0000 0.1602
-3.750 -0.5036 0.01640 0.00723 0.0153 1.0000 0.2355
-3.500 -0.5008 0.01382 0.00688 0.0202 1.0000 0.6074
-3.250 -0.4806 0.01390 0.00754 0.0243 1.0000 0.7826
-3.000 -0.4552 0.01451 0.00815 0.0272 1.0000 0.8537
-2.750 -0.4072 0.01581 0.00929 0.0266 1.0000 0.9096
-2.500 -0.3137 0.01697 0.01008 0.0159 1.0000 0.9365
-2.250 -0.2065 0.01757 0.01036 0.0015 1.0000 0.9612
-2.000 -0.1212 0.01746 0.01002 -0.0098 1.0000 0.9822
-1.750 -0.0421 0.01690 0.00931 -0.0206 1.0000 0.9976
-1.500 -0.0215 0.01657 0.00894 -0.0205 1.0000 1.0000
-1.250 -0.0137 0.01635 0.00871 -0.0179 1.0000 1.0000
-1.000 -0.0078 0.01617 0.00854 -0.0149 1.0000 1.0000
-0.750 -0.0038 0.01605 0.00841 -0.0116 1.0000 1.0000
-0.500 -0.0016 0.01596 0.00833 -0.0079 1.0000 1.0000
-0.250 -0.0005 0.01592 0.00828 -0.0040 1.0000 1.0000
0.000 0.0000 0.01590 0.00827 0.0000 1.0000 1.0000
0.250 0.0005 0.01592 0.00828 0.0040 1.0000 1.0000
0.500 0.0015 0.01596 0.00833 0.0079 1.0000 1.0000
0.750 0.0038 0.01605 0.00841 0.0116 1.0000 1.0000
1.000 0.0078 0.01617 0.00854 0.0149 1.0000 1.0000
1.250 0.0137 0.01634 0.00871 0.0179 1.0000 1.0000
1.500 0.0215 0.01657 0.00894 0.0205 1.0000 1.0000
1.750 0.0420 0.01690 0.00930 0.0206 0.9976 1.0000
2.000 0.1212 0.01746 0.01002 0.0098 0.9822 1.0000
2.250 0.2064 0.01757 0.01035 -0.0015 0.9612 1.0000
2.500 0.3136 0.01697 0.01008 -0.0158 0.9366 1.0000
2.750 0.4071 0.01581 0.00928 -0.0266 0.9096 1.0000
3.000 0.4551 0.01451 0.00815 -0.0272 0.8538 1.0000
3.250 0.4805 0.01390 0.00754 -0.0243 0.7828 1.0000
3.500 0.5007 0.01382 0.00688 -0.0202 0.6077 1.0000
3.750 0.5035 0.01640 0.00723 -0.0153 0.2358 1.0000
4.000 0.5174 0.01801 0.00821 -0.0129 0.1603 1.0000
4.250 0.5349 0.01908 0.00909 -0.0109 0.1364 1.0000
4.500 0.5541 0.02004 0.00994 -0.0093 0.1225 1.0000
4.750 0.5748 0.02117 0.01090 -0.0080 0.1141 1.0000
5.000 0.5977 0.02226 0.01208 -0.0068 0.1085 1.0000
5.250 0.6202 0.02333 0.01320 -0.0057 0.1029 1.0000
5.500 0.6431 0.02489 0.01471 -0.0048 0.0980 1.0000
5.750 0.6657 0.02622 0.01631 -0.0034 0.0952 1.0000
6.000 0.6875 0.02781 0.01816 -0.0020 0.0930 1.0000
6.250 0.7079 0.02935 0.01988 -0.0005 0.0899 1.0000
6.500 0.7274 0.03120 0.02179 0.0007 0.0865 1.0000
6.750 0.7451 0.03410 0.02495 0.0023 0.0855 1.0000
7.000 0.7602 0.03708 0.02826 0.0044 0.0852 1.0000
7.250 0.7721 0.03918 0.03086 0.0073 0.0843 1.0000
7.500 0.7817 0.04189 0.03402 0.0102 0.0837 1.0000
7.750 0.7920 0.04599 0.03833 0.0123 0.0848 1.0000
8.000 0.7863 0.05187 0.04529 0.0176 0.1014 1.0000
8.750 0.6809 0.07892 0.07390 0.0180 0.1798 1.0000
9.000 0.5393 0.07788 0.07300 0.0190 0.1905 1.0000
9.250 0.6752 0.08712 0.08206 0.0181 0.1695 1.0000
9.500 0.6439 0.09342 0.08825 0.0111 0.1628 1.0000
9.750 0.6802 0.09500 0.08990 0.0184 0.1559 1.0000
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Polar data table (+)
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