NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 50,000 Max Cl/Cd: 25.59 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0009sm-il-50000-n5.txt Download as CSV file: xf-n0009sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7052 0.09236 0.08512 -0.0179 1.0000 0.0549
-10.750 -0.7211 0.08514 0.07791 -0.0227 1.0000 0.0547
-10.500 -0.7400 0.07872 0.07148 -0.0268 1.0000 0.0545
-10.250 -0.7592 0.07349 0.06619 -0.0289 1.0000 0.0542
-10.000 -0.7814 0.06901 0.06161 -0.0289 1.0000 0.0541
-9.750 -0.8024 0.06479 0.05718 -0.0278 1.0000 0.0543
-9.500 -0.8195 0.06046 0.05250 -0.0263 1.0000 0.0549
-9.250 -0.8115 0.05818 0.05031 -0.0252 1.0000 0.0578
-9.000 -0.8100 0.05532 0.04727 -0.0237 1.0000 0.0603
-8.750 -0.8118 0.05155 0.04313 -0.0219 1.0000 0.0620
-8.500 -0.8104 0.04777 0.03887 -0.0199 1.0000 0.0638
-8.250 -0.8068 0.04435 0.03477 -0.0176 1.0000 0.0671
-8.000 -0.7934 0.04213 0.03248 -0.0163 1.0000 0.0715
-7.750 -0.7791 0.03970 0.02974 -0.0147 1.0000 0.0754
-7.500 -0.7631 0.03704 0.02656 -0.0131 1.0000 0.0788
-7.250 -0.7453 0.03501 0.02430 -0.0118 1.0000 0.0839
-7.000 -0.7263 0.03341 0.02249 -0.0105 1.0000 0.0905
-6.750 -0.7045 0.03149 0.02019 -0.0093 1.0000 0.0954
-6.500 -0.6826 0.02993 0.01859 -0.0083 1.0000 0.1006
-6.250 -0.6608 0.02858 0.01703 -0.0072 1.0000 0.1092
-6.000 -0.6398 0.02740 0.01579 -0.0060 1.0000 0.1191
-5.750 -0.6182 0.02614 0.01452 -0.0048 1.0000 0.1280
-5.500 -0.5969 0.02499 0.01331 -0.0035 1.0000 0.1394
-5.250 -0.5768 0.02395 0.01226 -0.0022 1.0000 0.1585
-5.000 -0.5569 0.02284 0.01127 -0.0010 1.0000 0.1842
-4.750 -0.5376 0.02172 0.01035 0.0004 1.0000 0.2218
-4.500 -0.5199 0.02064 0.00963 0.0019 1.0000 0.2844
-4.250 -0.5026 0.01974 0.00907 0.0037 1.0000 0.3595
-4.000 -0.4866 0.01901 0.00868 0.0061 1.0000 0.4351
-3.750 -0.4702 0.01842 0.00836 0.0086 1.0000 0.5100
-3.500 -0.4531 0.01795 0.00818 0.0114 1.0000 0.5859
-3.250 -0.4338 0.01761 0.00811 0.0141 1.0000 0.6598
-3.000 -0.4102 0.01743 0.00809 0.0163 1.0000 0.7274
-2.750 -0.3798 0.01740 0.00807 0.0171 1.0000 0.7852
-2.500 -0.3402 0.01751 0.00809 0.0161 1.0000 0.8338
-2.250 -0.2955 0.01765 0.00807 0.0137 1.0000 0.8745
-2.000 -0.2469 0.01779 0.00798 0.0102 1.0000 0.9084
-1.750 -0.1932 0.01786 0.00785 0.0053 1.0000 0.9359
-1.500 -0.1400 0.01780 0.00762 0.0001 1.0000 0.9605
-1.250 -0.0872 0.01764 0.00730 -0.0053 1.0000 0.9832
-1.000 -0.0393 0.01739 0.00695 -0.0102 1.0000 1.0000
-0.750 -0.0297 0.01719 0.00674 -0.0077 1.0000 1.0000
-0.500 -0.0199 0.01705 0.00658 -0.0052 1.0000 1.0000
-0.250 -0.0100 0.01696 0.00649 -0.0026 1.0000 1.0000
0.000 0.0000 0.01694 0.00646 0.0000 1.0000 1.0000
0.250 0.0100 0.01696 0.00649 0.0026 1.0000 1.0000
0.500 0.0199 0.01704 0.00658 0.0052 1.0000 1.0000
0.750 0.0297 0.01718 0.00674 0.0077 1.0000 1.0000
1.000 0.0393 0.01739 0.00695 0.0102 1.0000 1.0000
1.250 0.0871 0.01763 0.00730 0.0054 0.9832 1.0000
1.500 0.1399 0.01779 0.00762 -0.0001 0.9606 1.0000
1.750 0.1931 0.01785 0.00785 -0.0053 0.9360 1.0000
2.000 0.2470 0.01778 0.00798 -0.0102 0.9084 1.0000
2.250 0.2955 0.01765 0.00806 -0.0137 0.8745 1.0000
2.500 0.3402 0.01750 0.00808 -0.0161 0.8337 1.0000
2.750 0.3797 0.01740 0.00807 -0.0171 0.7852 1.0000
3.000 0.4102 0.01743 0.00809 -0.0163 0.7276 1.0000
3.250 0.4337 0.01760 0.00811 -0.0141 0.6598 1.0000
3.500 0.4530 0.01795 0.00818 -0.0114 0.5858 1.0000
3.750 0.4701 0.01842 0.00836 -0.0086 0.5103 1.0000
4.000 0.4865 0.01901 0.00868 -0.0060 0.4349 1.0000
4.250 0.5025 0.01973 0.00907 -0.0037 0.3598 1.0000
4.500 0.5198 0.02064 0.00963 -0.0019 0.2843 1.0000
4.750 0.5375 0.02172 0.01035 -0.0003 0.2216 1.0000
5.000 0.5569 0.02284 0.01127 0.0010 0.1839 1.0000
5.250 0.5767 0.02394 0.01225 0.0023 0.1585 1.0000
5.500 0.5969 0.02500 0.01332 0.0035 0.1394 1.0000
5.750 0.6181 0.02615 0.01452 0.0048 0.1280 1.0000
6.000 0.6397 0.02740 0.01579 0.0060 0.1190 1.0000
6.250 0.6608 0.02859 0.01704 0.0072 0.1092 1.0000
6.500 0.6825 0.02993 0.01858 0.0083 0.1006 1.0000
6.750 0.7045 0.03149 0.02018 0.0093 0.0954 1.0000
7.000 0.7264 0.03341 0.02249 0.0105 0.0905 1.0000
7.250 0.7453 0.03500 0.02429 0.0118 0.0838 1.0000
7.500 0.7631 0.03703 0.02655 0.0131 0.0788 1.0000
7.750 0.7792 0.03971 0.02974 0.0147 0.0754 1.0000
8.000 0.7935 0.04213 0.03247 0.0163 0.0714 1.0000
8.250 0.8071 0.04436 0.03476 0.0176 0.0672 1.0000
8.500 0.8104 0.04779 0.03889 0.0199 0.0638 1.0000
8.750 0.8118 0.05159 0.04317 0.0219 0.0620 1.0000
9.000 0.8103 0.05529 0.04724 0.0237 0.0602 1.0000
9.250 0.8110 0.05830 0.05045 0.0252 0.0579 1.0000
9.500 0.8195 0.06051 0.05255 0.0262 0.0548 1.0000
9.750 0.8020 0.06486 0.05726 0.0277 0.0543 1.0000
10.000 0.7821 0.06904 0.06163 0.0288 0.0541 1.0000
10.250 0.7602 0.07349 0.06618 0.0288 0.0542 1.0000
10.500 0.7394 0.07888 0.07164 0.0265 0.0544 1.0000
10.750 0.7210 0.08528 0.07805 0.0225 0.0547 1.0000
11.000 0.7050 0.09259 0.08535 0.0175 0.0549 1.0000
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Polar data table (+)
Polar graphs
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