NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 100,000 Max Cl/Cd: 35.74 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034-il-100000.txt Download as CSV file: xf-naca001034-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
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 -0.5179 0.09660 0.09201 -0.0216 1.0000 0.1418
-9.750 -0.5072 0.09289 0.08830 -0.0199 1.0000 0.1493
-9.500 -0.5338 0.08764 0.08314 -0.0237 1.0000 0.1554
-9.250 -0.5201 0.08414 0.07963 -0.0213 1.0000 0.1639
-6.250 -0.6980 0.03723 0.02932 -0.0038 1.0000 0.0718
-6.000 -0.6792 0.03400 0.02538 -0.0005 1.0000 0.0609
-5.750 -0.6597 0.03088 0.02190 0.0017 1.0000 0.0573
-5.500 -0.6376 0.02833 0.01889 0.0037 1.0000 0.0547
-5.250 -0.6134 0.02619 0.01645 0.0052 1.0000 0.0542
-5.000 -0.5907 0.02461 0.01478 0.0064 1.0000 0.0584
-4.750 -0.5671 0.02320 0.01315 0.0078 1.0000 0.0619
-4.500 -0.5443 0.02156 0.01149 0.0092 1.0000 0.0643
-4.250 -0.5274 0.02006 0.01012 0.0113 1.0000 0.0694
-4.000 -0.5114 0.01897 0.00901 0.0136 1.0000 0.0796
-3.750 -0.4951 0.01783 0.00790 0.0158 1.0000 0.1003
-3.500 -0.4972 0.01392 0.00685 0.0210 1.0000 0.5658
-3.250 -0.4830 0.01427 0.00815 0.0286 1.0000 0.8296
-3.000 -0.3623 0.01795 0.01123 0.0189 1.0000 0.9241
-2.750 -0.3016 0.01807 0.01101 0.0124 1.0000 0.9392
-2.500 -0.2440 0.01801 0.01064 0.0061 1.0000 0.9527
-2.250 -0.1886 0.01780 0.01021 0.0000 1.0000 0.9648
-2.000 -0.1352 0.01748 0.00972 -0.0060 1.0000 0.9763
-1.750 -0.0829 0.01709 0.00918 -0.0120 1.0000 0.9873
-1.500 -0.0299 0.01665 0.00863 -0.0182 1.0000 0.9974
-1.250 -0.0099 0.01635 0.00830 -0.0181 1.0000 1.0000
-1.000 -0.0045 0.01616 0.00810 -0.0151 1.0000 1.0000
-0.750 -0.0013 0.01602 0.00796 -0.0118 1.0000 1.0000
-0.500 0.0002 0.01593 0.00787 -0.0080 1.0000 1.0000
-0.250 0.0005 0.01588 0.00782 -0.0041 1.0000 1.0000
0.000 0.0000 0.01587 0.00780 0.0000 1.0000 1.0000
0.250 -0.0004 0.01588 0.00782 0.0041 1.0000 1.0000
0.500 -0.0002 0.01593 0.00787 0.0080 1.0000 1.0000
0.750 0.0013 0.01602 0.00796 0.0118 1.0000 1.0000
1.000 0.0045 0.01616 0.00810 0.0151 1.0000 1.0000
1.250 0.0099 0.01634 0.00830 0.0181 1.0000 1.0000
1.500 0.0298 0.01664 0.00863 0.0182 0.9975 1.0000
1.750 0.0828 0.01708 0.00917 0.0120 0.9873 1.0000
2.000 0.1351 0.01747 0.00972 0.0060 0.9763 1.0000
2.250 0.1886 0.01779 0.01020 0.0001 0.9649 1.0000
2.500 0.2440 0.01800 0.01063 -0.0061 0.9527 1.0000
2.750 0.3016 0.01807 0.01101 -0.0124 0.9392 1.0000
3.000 0.3624 0.01794 0.01123 -0.0189 0.9242 1.0000
3.250 0.4830 0.01426 0.00814 -0.0286 0.8296 1.0000
3.500 0.4971 0.01391 0.00684 -0.0210 0.5659 1.0000
3.750 0.4951 0.01782 0.00790 -0.0158 0.1003 1.0000
4.000 0.5113 0.01896 0.00900 -0.0136 0.0796 1.0000
4.250 0.5273 0.02006 0.01012 -0.0113 0.0694 1.0000
4.500 0.5443 0.02155 0.01148 -0.0092 0.0643 1.0000
4.750 0.5670 0.02320 0.01315 -0.0078 0.0619 1.0000
5.000 0.5907 0.02461 0.01478 -0.0064 0.0585 1.0000
5.250 0.6133 0.02619 0.01645 -0.0052 0.0542 1.0000
5.500 0.6375 0.02832 0.01888 -0.0037 0.0547 1.0000
5.750 0.6596 0.03087 0.02190 -0.0016 0.0573 1.0000
6.000 0.6791 0.03399 0.02538 0.0005 0.0609 1.0000
6.250 0.6979 0.03722 0.02931 0.0038 0.0718 1.0000
8.750 0.7468 0.08061 0.07567 0.0264 0.1296 1.0000
9.000 0.7075 0.08312 0.07837 0.0271 0.1288 1.0000
9.250 0.6719 0.08711 0.08241 0.0257 0.1280 1.0000
9.500 0.6427 0.09378 0.08903 0.0182 0.1261 1.0000
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Polar data table (+)
Polar graphs
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