NACA 16009 (naca16009-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 500,000 Max Cl/Cd: 44.64 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16009-il-500000.txt Download as CSV file: xf-naca16009-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.7033 0.06222 0.05958 -0.0196 1.0000 0.0145
-7.750 -0.7122 0.05938 0.05661 -0.0152 1.0000 0.0146
-7.500 -0.7195 0.05644 0.05352 -0.0107 1.0000 0.0146
-7.250 -0.7251 0.05344 0.05035 -0.0063 1.0000 0.0146
-7.000 -0.7290 0.05038 0.04710 -0.0019 1.0000 0.0147
-5.000 -0.6171 0.02028 0.01423 0.0140 0.9891 0.0138
-4.750 -0.5903 0.01778 0.01142 0.0146 0.9883 0.0132
-4.500 -0.5624 0.01615 0.00961 0.0148 0.9873 0.0133
-4.250 -0.5335 0.01512 0.00845 0.0146 0.9861 0.0142
-4.000 -0.5060 0.01401 0.00721 0.0146 0.9848 0.0154
-3.750 -0.4778 0.01308 0.00618 0.0143 0.9837 0.0187
-3.500 -0.4461 0.01262 0.00565 0.0132 0.9826 0.0226
-3.250 -0.4230 0.01193 0.00495 0.0142 0.9796 0.0408
-3.000 -0.3983 0.01129 0.00463 0.0144 0.9768 0.1131
-2.750 -0.3758 0.01012 0.00433 0.0146 0.9745 0.3188
-2.500 -0.3638 0.00815 0.00403 0.0171 0.9723 0.7090
-2.250 -0.3379 0.00788 0.00428 0.0181 0.9710 0.8576
-2.000 -0.3050 0.00800 0.00439 0.0172 0.9698 0.8866
-1.750 -0.2770 0.00820 0.00458 0.0174 0.9675 0.9090
-1.500 -0.2524 0.00840 0.00475 0.0184 0.9638 0.9249
-1.250 -0.2204 0.00861 0.00490 0.0176 0.9617 0.9342
-1.000 -0.1784 0.00928 0.00556 0.0153 0.9622 0.9490
-0.750 -0.1241 0.00989 0.00613 0.0099 0.9649 0.9577
-0.500 -0.0789 0.01002 0.00623 0.0058 0.9649 0.9590
-0.250 -0.0389 0.01007 0.00626 0.0028 0.9637 0.9606
0.000 0.0000 0.01008 0.00626 0.0000 0.9621 0.9621
0.250 0.0389 0.01007 0.00626 -0.0028 0.9606 0.9637
0.500 0.0789 0.01002 0.00623 -0.0058 0.9590 0.9649
0.750 0.1241 0.00989 0.00613 -0.0099 0.9577 0.9649
1.000 0.1783 0.00929 0.00556 -0.0153 0.9490 0.9622
1.250 0.2204 0.00860 0.00490 -0.0176 0.9342 0.9617
1.500 0.2524 0.00840 0.00475 -0.0184 0.9251 0.9638
1.750 0.2767 0.00820 0.00458 -0.0173 0.9086 0.9676
2.000 0.3051 0.00800 0.00439 -0.0172 0.8865 0.9699
2.250 0.3379 0.00788 0.00428 -0.0181 0.8577 0.9711
2.500 0.3638 0.00815 0.00403 -0.0171 0.7095 0.9723
2.750 0.3759 0.01010 0.00433 -0.0146 0.3222 0.9745
3.000 0.3983 0.01129 0.00463 -0.0144 0.1128 0.9768
3.250 0.4228 0.01193 0.00495 -0.0142 0.0406 0.9797
3.500 0.4461 0.01262 0.00565 -0.0132 0.0227 0.9826
3.750 0.4779 0.01306 0.00616 -0.0143 0.0186 0.9837
4.000 0.5060 0.01400 0.00721 -0.0146 0.0154 0.9849
4.250 0.5336 0.01513 0.00846 -0.0146 0.0142 0.9861
4.500 0.5624 0.01615 0.00960 -0.0148 0.0134 0.9874
4.750 0.5904 0.01777 0.01142 -0.0146 0.0132 0.9883
5.000 0.6172 0.02026 0.01421 -0.0140 0.0138 0.9892
5.500 0.6552 0.03268 0.02776 -0.0091 0.0242 0.9919
5.750 0.6887 0.03065 0.02599 -0.0089 0.0204 0.9942
6.000 0.7128 0.03312 0.02878 -0.0086 0.0182 0.9956
6.250 0.7348 0.03524 0.03107 -0.0087 0.0167 0.9974
6.500 0.7519 0.03843 0.03445 -0.0086 0.0156 0.9994
6.750 0.7310 0.04727 0.04377 -0.0025 0.0147 1.0000
7.000 0.7289 0.05037 0.04709 0.0019 0.0147 1.0000
7.250 0.7250 0.05343 0.05034 0.0063 0.0146 1.0000
7.500 0.7194 0.05644 0.05351 0.0108 0.0146 1.0000
7.750 0.7121 0.05937 0.05659 0.0152 0.0146 1.0000
8.000 0.7033 0.06221 0.05956 0.0196 0.0145 1.0000
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Polar data table (+)
Polar graphs
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