AG11 (ag11-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 50,000 Max Cl/Cd: 33.02 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag11-il-50000.txt Download as CSV file: xf-ag11-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG11
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5272 0.10598 0.09946 0.0114 1.0000 0.1518
-7.500 -0.5205 0.10187 0.09538 0.0108 1.0000 0.1570
-7.250 -0.5173 0.09911 0.09268 0.0079 1.0000 0.1662
-7.000 -0.5070 0.09484 0.08846 0.0086 1.0000 0.1748
-6.750 -0.5046 0.09186 0.08555 0.0026 1.0000 0.1836
-6.500 -0.4980 0.08924 0.08293 -0.0030 1.0000 0.1965
-6.250 -0.4875 0.08504 0.07881 -0.0023 1.0000 0.2112
-6.000 -0.4759 0.08080 0.07464 0.0005 1.0000 0.2276
-5.750 -0.4647 0.07728 0.07117 0.0017 1.0000 0.2475
-5.500 -0.4556 0.07388 0.06782 0.0006 1.0000 0.2712
-5.250 -0.4458 0.07060 0.06460 0.0015 1.0000 0.2997
-5.000 -0.4357 0.06744 0.06153 0.0046 1.0000 0.3333
-4.750 -0.4277 0.06449 0.05864 0.0085 1.0000 0.3767
-4.500 -0.1443 0.04397 0.03753 0.0139 1.0000 1.0000
-4.250 -0.1308 0.04149 0.03510 0.0123 1.0000 1.0000
-4.000 -0.1316 0.04007 0.03377 0.0141 1.0000 0.9938
-3.750 -0.1820 0.04177 0.03567 0.0268 1.0000 0.9484
-3.500 -0.2291 0.04274 0.03686 0.0361 1.0000 0.8909
-3.250 -0.2743 0.04306 0.03741 0.0424 1.0000 0.8304
-3.000 -0.1864 0.03539 0.02718 -0.0354 1.0000 0.1769
-2.750 -0.1477 0.03249 0.02342 -0.0363 1.0000 0.1373
-2.500 -0.1160 0.03028 0.02054 -0.0360 1.0000 0.1245
-2.250 -0.0890 0.02779 0.01789 -0.0355 1.0000 0.1209
-2.000 -0.0604 0.02577 0.01550 -0.0348 1.0000 0.1153
-1.750 -0.0317 0.02426 0.01352 -0.0337 1.0000 0.1116
-1.500 -0.0051 0.02257 0.01172 -0.0328 1.0000 0.1137
-1.250 0.0208 0.02134 0.01034 -0.0316 1.0000 0.1237
-1.000 0.0483 0.01999 0.00896 -0.0306 1.0000 0.1357
-0.750 0.0747 0.01876 0.00779 -0.0298 1.0000 0.1675
-0.500 0.1011 0.01463 0.00627 -0.0277 1.0000 1.0000
-0.250 0.1251 0.01477 0.00573 -0.0267 1.0000 1.0000
0.000 0.1480 0.01494 0.00557 -0.0260 1.0000 1.0000
0.250 0.1705 0.01516 0.00553 -0.0255 1.0000 1.0000
0.500 0.1928 0.01543 0.00563 -0.0251 1.0000 1.0000
0.750 0.2147 0.01578 0.00584 -0.0249 1.0000 1.0000
1.000 0.2360 0.01620 0.00616 -0.0248 1.0000 1.0000
1.250 0.2566 0.01673 0.00661 -0.0249 1.0000 1.0000
1.500 0.2764 0.01739 0.00722 -0.0252 1.0000 1.0000
1.750 0.2952 0.01820 0.00802 -0.0259 1.0000 1.0000
2.000 0.3511 0.01913 0.00898 -0.0335 0.9798 1.0000
2.250 0.4393 0.01955 0.00955 -0.0454 0.9357 1.0000
2.500 0.5130 0.01943 0.00965 -0.0527 0.8904 1.0000
2.750 0.5590 0.01924 0.00955 -0.0535 0.8441 1.0000
3.000 0.5875 0.01922 0.00952 -0.0510 0.7967 1.0000
3.250 0.6099 0.01934 0.00957 -0.0474 0.7485 1.0000
3.500 0.6308 0.01955 0.00964 -0.0437 0.7009 1.0000
3.750 0.6514 0.01995 0.00995 -0.0406 0.6501 1.0000
4.000 0.6729 0.02042 0.01020 -0.0377 0.6012 1.0000
4.250 0.6947 0.02104 0.01065 -0.0353 0.5504 1.0000
4.500 0.7170 0.02175 0.01111 -0.0332 0.5028 1.0000
4.750 0.7395 0.02259 0.01174 -0.0314 0.4560 1.0000
5.000 0.7623 0.02356 0.01262 -0.0298 0.4113 1.0000
5.250 0.7853 0.02465 0.01352 -0.0285 0.3709 1.0000
5.500 0.8087 0.02588 0.01464 -0.0273 0.3340 1.0000
5.750 0.8320 0.02721 0.01584 -0.0263 0.3013 1.0000
6.000 0.8562 0.02879 0.01740 -0.0254 0.2750 1.0000
6.250 0.8794 0.03044 0.01923 -0.0246 0.2503 1.0000
6.500 0.9031 0.03229 0.02113 -0.0239 0.2315 1.0000
6.750 0.9266 0.03462 0.02370 -0.0233 0.2175 1.0000
7.000 0.9487 0.03685 0.02622 -0.0226 0.2034 1.0000
7.250 0.9709 0.03908 0.02856 -0.0220 0.1912 1.0000
7.500 0.9874 0.04302 0.03334 -0.0216 0.1846 1.0000
7.750 1.0091 0.04587 0.03625 -0.0209 0.1780 1.0000
8.000 1.0166 0.05084 0.04207 -0.0208 0.1727 1.0000
8.250 1.0388 0.05303 0.04413 -0.0199 0.1638 1.0000
8.500 1.0415 0.05897 0.05075 -0.0202 0.1632 1.0000
8.750 1.0425 0.06516 0.05739 -0.0207 0.1635 1.0000
9.000 0.9952 0.07776 0.07062 -0.0273 0.1732 1.0000
9.250 0.9778 0.08634 0.07932 -0.0318 0.1795 1.0000
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Polar data table (+)
Polar graphs
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