NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 50,000 Max Cl/Cd: 24.86 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65209-il-50000.txt Download as CSV file: xf-naca65209-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5160 0.11108 0.10406 -0.0045 1.0000 0.2735
-9.250 -0.5085 0.10777 0.10078 -0.0039 1.0000 0.2927
-9.000 -0.5166 0.10573 0.09884 -0.0041 1.0000 0.3110
-8.750 -0.4985 0.10174 0.09483 -0.0023 1.0000 0.3370
-8.500 -0.4871 0.09830 0.09142 -0.0008 1.0000 0.3635
-8.250 -0.4775 0.09497 0.08807 0.0004 1.0000 0.3879
-7.500 -0.4495 0.08576 0.07896 0.0048 1.0000 0.4694
-5.750 -0.5404 0.04724 0.03950 -0.0332 1.0000 0.1686
-5.500 -0.5222 0.04317 0.03454 -0.0327 1.0000 0.1424
-5.250 -0.5030 0.03996 0.03059 -0.0313 1.0000 0.1293
-5.000 -0.4839 0.03659 0.02702 -0.0301 1.0000 0.1244
-4.750 -0.4631 0.03389 0.02381 -0.0287 1.0000 0.1199
-4.500 -0.4423 0.03172 0.02131 -0.0274 1.0000 0.1223
-4.250 -0.4203 0.02976 0.01899 -0.0260 1.0000 0.1247
-4.000 -0.3969 0.02792 0.01683 -0.0246 1.0000 0.1253
-3.750 -0.3729 0.02634 0.01499 -0.0230 1.0000 0.1278
-3.500 -0.3502 0.02484 0.01351 -0.0213 1.0000 0.1347
-3.250 -0.0886 0.02047 0.01131 -0.0408 1.0000 1.0000
-3.000 -0.0803 0.02011 0.01079 -0.0390 1.0000 1.0000
-2.750 -0.0743 0.01983 0.01038 -0.0367 1.0000 1.0000
-2.500 -0.0710 0.01961 0.01006 -0.0340 1.0000 1.0000
-2.250 -0.0711 0.01945 0.00982 -0.0307 1.0000 1.0000
-2.000 -0.0741 0.01932 0.00963 -0.0270 1.0000 1.0000
-1.750 -0.0792 0.01920 0.00946 -0.0230 1.0000 1.0000
-1.500 -0.0855 0.01907 0.00927 -0.0187 1.0000 1.0000
-1.250 -0.0922 0.01892 0.00906 -0.0145 1.0000 1.0000
-1.000 -0.0981 0.01875 0.00882 -0.0103 1.0000 1.0000
-0.750 -0.1010 0.01860 0.00854 -0.0066 1.0000 1.0000
-0.500 -0.0971 0.01853 0.00835 -0.0039 1.0000 1.0000
-0.250 -0.0860 0.01858 0.00824 -0.0025 1.0000 1.0000
0.000 -0.0707 0.01871 0.00823 -0.0016 1.0000 1.0000
0.250 -0.0531 0.01891 0.00829 -0.0012 1.0000 1.0000
0.500 -0.0343 0.01916 0.00843 -0.0009 1.0000 1.0000
0.750 -0.0149 0.01946 0.00861 -0.0007 1.0000 1.0000
1.000 0.0049 0.01980 0.00887 -0.0005 1.0000 1.0000
1.250 0.0249 0.02018 0.00918 -0.0005 1.0000 1.0000
1.500 0.0450 0.02060 0.00956 -0.0004 1.0000 1.0000
1.750 0.0650 0.02105 0.00999 -0.0004 1.0000 1.0000
2.000 0.0850 0.02154 0.01047 -0.0004 1.0000 1.0000
2.250 0.1049 0.02207 0.01101 -0.0004 1.0000 1.0000
2.500 0.1247 0.02264 0.01161 -0.0005 1.0000 1.0000
2.750 0.1442 0.02325 0.01226 -0.0005 1.0000 1.0000
3.000 0.1636 0.02391 0.01301 -0.0006 1.0000 1.0000
3.250 0.1827 0.02461 0.01379 -0.0008 1.0000 1.0000
3.500 0.2016 0.02536 0.01464 -0.0009 1.0000 1.0000
3.750 0.2200 0.02617 0.01556 -0.0011 1.0000 1.0000
4.000 0.2695 0.02788 0.01755 -0.0073 0.9842 1.0000
4.250 0.3174 0.02946 0.01948 -0.0129 0.9654 1.0000
4.500 0.3704 0.03107 0.02150 -0.0191 0.9429 1.0000
4.750 0.5846 0.02352 0.01221 -0.0175 0.1805 1.0000
5.000 0.6028 0.02538 0.01381 -0.0158 0.1494 1.0000
5.250 0.6346 0.02730 0.01569 -0.0154 0.1340 1.0000
5.500 0.6733 0.02942 0.01786 -0.0157 0.1231 1.0000
5.750 0.7067 0.03180 0.02037 -0.0158 0.1143 1.0000
6.000 0.7380 0.03444 0.02336 -0.0154 0.1123 1.0000
6.250 0.7660 0.03739 0.02675 -0.0146 0.1129 1.0000
6.500 0.7910 0.04070 0.03057 -0.0136 0.1146 1.0000
6.750 0.8114 0.04402 0.03439 -0.0124 0.1151 1.0000
7.000 0.8288 0.04757 0.03842 -0.0111 0.1158 1.0000
7.250 0.8448 0.05139 0.04284 -0.0096 0.1219 1.0000
7.500 0.8606 0.05677 0.04856 -0.0088 0.1317 1.0000
7.750 0.8577 0.06174 0.05458 -0.0075 0.1535 1.0000
8.000 0.8565 0.06889 0.06234 -0.0088 0.1898 1.0000
8.250 0.8208 0.07648 0.07032 -0.0128 0.2214 1.0000
8.500 0.7233 0.09186 0.08546 -0.0329 0.3215 1.0000
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Polar data table (+)
Polar graphs
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