NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 50,000 Max Cl/Cd: 22.09 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66209-il-50000.txt Download as CSV file: xf-naca66209-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5087 0.12186 0.11466 -0.0156 1.0000 0.2205
-10.250 -0.5244 0.12067 0.11358 -0.0176 1.0000 0.2293
-10.000 -0.5176 0.11679 0.10973 -0.0172 1.0000 0.2431
-9.750 -0.5118 0.11323 0.10621 -0.0169 1.0000 0.2569
-9.500 -0.5108 0.11012 0.10315 -0.0167 1.0000 0.2712
-9.250 -0.4974 0.10575 0.09879 -0.0155 1.0000 0.2884
-9.000 -0.4884 0.10244 0.09550 -0.0142 1.0000 0.3103
-8.750 -0.4800 0.09910 0.09215 -0.0127 1.0000 0.3345
-8.500 -0.4728 0.09615 0.08924 -0.0110 1.0000 0.3622
-8.250 -0.4651 0.09325 0.08638 -0.0088 1.0000 0.3940
-8.000 -0.4623 0.09082 0.08400 -0.0066 1.0000 0.4248
-7.750 -0.4510 0.08754 0.08075 -0.0044 1.0000 0.4568
-7.500 -0.4305 0.08403 0.07723 -0.0025 1.0000 0.4912
-7.000 -0.4036 0.07793 0.07116 0.0013 1.0000 0.5578
-6.250 -0.3773 0.05797 0.05212 -0.0024 1.0000 0.4885
-6.000 -0.4466 0.05526 0.04970 -0.0005 1.0000 0.4304
-5.750 -0.4917 0.05244 0.04707 0.0020 1.0000 0.4149
-5.250 -0.5742 0.04760 0.04004 -0.0204 1.0000 0.1941
-5.000 -0.5514 0.04333 0.03481 -0.0204 1.0000 0.1551
-4.750 -0.5302 0.03981 0.03064 -0.0192 1.0000 0.1377
-4.500 -0.5079 0.03701 0.02720 -0.0178 1.0000 0.1273
-4.250 -0.4846 0.03439 0.02394 -0.0165 1.0000 0.1204
-4.000 -0.4612 0.03225 0.02134 -0.0152 1.0000 0.1200
-3.750 -0.4383 0.03031 0.01921 -0.0141 1.0000 0.1244
-3.500 -0.4132 0.02859 0.01717 -0.0129 1.0000 0.1257
-3.250 -0.3869 0.02705 0.01534 -0.0116 1.0000 0.1282
-3.000 -0.1380 0.02162 0.01272 -0.0352 1.0000 1.0000
-2.750 -0.1339 0.02148 0.01224 -0.0320 1.0000 1.0000
-2.500 -0.1299 0.02135 0.01188 -0.0288 1.0000 1.0000
-2.250 -0.1259 0.02122 0.01154 -0.0256 1.0000 1.0000
-2.000 -0.1217 0.02110 0.01124 -0.0224 1.0000 1.0000
-1.750 -0.1174 0.02098 0.01096 -0.0192 1.0000 1.0000
-1.500 -0.1129 0.02087 0.01069 -0.0161 1.0000 1.0000
-1.250 -0.1083 0.02075 0.01043 -0.0129 1.0000 1.0000
-1.000 -0.1034 0.02063 0.01016 -0.0098 1.0000 1.0000
-0.750 -0.0981 0.02052 0.00992 -0.0067 1.0000 1.0000
-0.500 -0.0922 0.02042 0.00970 -0.0038 1.0000 1.0000
-0.250 -0.0851 0.02033 0.00951 -0.0010 1.0000 1.0000
0.000 -0.0765 0.02028 0.00935 0.0016 1.0000 1.0000
0.250 -0.0654 0.02029 0.00925 0.0036 1.0000 1.0000
0.500 -0.0517 0.02035 0.00921 0.0052 1.0000 1.0000
0.750 -0.0360 0.02047 0.00922 0.0065 1.0000 1.0000
1.000 -0.0188 0.02064 0.00932 0.0074 1.0000 1.0000
1.250 -0.0007 0.02086 0.00948 0.0082 1.0000 1.0000
1.500 0.0181 0.02112 0.00970 0.0088 1.0000 1.0000
1.750 0.0373 0.02142 0.00998 0.0093 1.0000 1.0000
2.000 0.0568 0.02175 0.01031 0.0098 1.0000 1.0000
2.250 0.0765 0.02213 0.01070 0.0102 1.0000 1.0000
2.500 0.0961 0.02255 0.01115 0.0105 1.0000 1.0000
2.750 0.1157 0.02300 0.01166 0.0108 1.0000 1.0000
3.000 0.1352 0.02350 0.01223 0.0110 1.0000 1.0000
3.250 0.1546 0.02405 0.01290 0.0112 1.0000 1.0000
3.500 0.1736 0.02465 0.01361 0.0113 1.0000 1.0000
3.750 0.1923 0.02530 0.01439 0.0114 1.0000 1.0000
4.000 0.2107 0.02602 0.01526 0.0115 1.0000 1.0000
4.250 0.2284 0.02681 0.01622 0.0115 1.0000 1.0000
4.500 0.2458 0.02768 0.01733 0.0115 1.0000 1.0000
4.750 0.2624 0.02864 0.01850 0.0114 1.0000 1.0000
5.000 0.3230 0.03097 0.02137 0.0027 0.9747 1.0000
5.250 0.6248 0.02828 0.01650 -0.0123 0.1274 1.0000
5.500 0.6663 0.03062 0.01893 -0.0136 0.1162 1.0000
5.750 0.7016 0.03318 0.02179 -0.0138 0.1136 1.0000
6.000 0.7311 0.03594 0.02497 -0.0131 0.1139 1.0000
6.250 0.7561 0.03887 0.02838 -0.0120 0.1149 1.0000
6.500 0.7765 0.04181 0.03176 -0.0104 0.1139 1.0000
6.750 0.7938 0.04509 0.03562 -0.0086 0.1157 1.0000
7.000 0.8132 0.04936 0.04013 -0.0075 0.1210 1.0000
7.250 0.8241 0.05329 0.04486 -0.0051 0.1333 1.0000
7.500 0.8305 0.05785 0.05023 -0.0030 0.1540 1.0000
8.000 0.8059 0.07205 0.06572 -0.0061 0.2492 1.0000
8.250 0.7575 0.07964 0.07339 -0.0114 0.2909 1.0000
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Polar data table (+)
Polar graphs
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