RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 50,000 Max Cl/Cd: 25.87 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil2-il-50000.txt Download as CSV file: xf-amsoil2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING AIRFOIL
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 -0.4904 0.11487 0.10715 0.0019 1.0000 0.3256
-9.250 -0.4934 0.11227 0.10460 0.0018 1.0000 0.3411
-9.000 -0.4883 0.10936 0.10173 0.0023 1.0000 0.3585
-8.500 -0.4631 0.10277 0.09518 0.0039 1.0000 0.3959
-8.250 -0.4513 0.09960 0.09203 0.0046 1.0000 0.4147
-8.000 -0.4360 0.09651 0.08895 0.0056 1.0000 0.4366
-7.750 -0.4539 0.09582 0.08836 0.0075 1.0000 0.4630
-7.250 -0.6103 0.06928 0.06185 -0.0266 1.0000 0.2477
-7.000 -0.6343 0.05939 0.05132 -0.0296 1.0000 0.1962
-6.750 -0.6270 0.05562 0.04743 -0.0283 1.0000 0.1886
-6.500 -0.6367 0.05136 0.04221 -0.0264 1.0000 0.1767
-6.250 -0.6275 0.04829 0.03892 -0.0247 1.0000 0.1762
-6.000 -0.6177 0.04555 0.03583 -0.0230 1.0000 0.1764
-5.750 -0.6052 0.04295 0.03286 -0.0214 1.0000 0.1766
-5.500 -0.5900 0.04053 0.03008 -0.0200 1.0000 0.1769
-5.250 -0.5732 0.03803 0.02763 -0.0189 1.0000 0.1806
-5.000 -0.5553 0.03622 0.02566 -0.0177 1.0000 0.1849
-4.750 -0.5357 0.03442 0.02355 -0.0166 1.0000 0.1888
-4.500 -0.5149 0.03294 0.02159 -0.0156 1.0000 0.1939
-4.250 -0.4937 0.03123 0.01996 -0.0148 1.0000 0.2013
-4.000 -0.4712 0.02999 0.01848 -0.0139 1.0000 0.2096
-3.750 -0.4484 0.02867 0.01719 -0.0131 1.0000 0.2202
-3.500 -0.4247 0.02757 0.01601 -0.0123 1.0000 0.2332
-3.250 -0.4005 0.02657 0.01506 -0.0115 1.0000 0.2502
-3.000 -0.3763 0.02555 0.01424 -0.0107 1.0000 0.2724
-2.750 -0.3528 0.02452 0.01341 -0.0099 1.0000 0.3047
-2.500 -0.3313 0.02303 0.01259 -0.0091 1.0000 0.3669
-2.250 -0.3328 0.02160 0.01358 0.0004 1.0000 0.7462
-2.000 -0.0880 0.02482 0.01577 -0.0252 1.0000 1.0000
-1.750 -0.0908 0.02469 0.01556 -0.0217 1.0000 1.0000
-1.500 -0.0934 0.02455 0.01536 -0.0182 1.0000 1.0000
-1.250 -0.0959 0.02441 0.01514 -0.0147 1.0000 1.0000
-1.000 -0.0980 0.02426 0.01493 -0.0112 1.0000 1.0000
-0.750 -0.0998 0.02411 0.01471 -0.0077 1.0000 1.0000
-0.500 -0.1009 0.02395 0.01449 -0.0043 1.0000 1.0000
-0.250 -0.1006 0.02381 0.01429 -0.0011 1.0000 1.0000
0.000 -0.0980 0.02372 0.01412 0.0017 1.0000 1.0000
0.250 -0.0904 0.02373 0.01405 0.0038 1.0000 1.0000
0.500 -0.0778 0.02387 0.01410 0.0050 1.0000 1.0000
0.750 -0.0619 0.02410 0.01426 0.0056 1.0000 1.0000
1.000 -0.0440 0.02443 0.01451 0.0060 1.0000 1.0000
1.250 -0.0248 0.02482 0.01484 0.0061 1.0000 1.0000
1.500 -0.0050 0.02528 0.01525 0.0061 1.0000 1.0000
1.750 0.0153 0.02579 0.01573 0.0060 1.0000 1.0000
2.000 0.0358 0.02636 0.01628 0.0058 1.0000 1.0000
2.250 0.0564 0.02698 0.01689 0.0056 1.0000 1.0000
2.500 0.0770 0.02765 0.01757 0.0053 1.0000 1.0000
2.750 0.0974 0.02837 0.01832 0.0050 1.0000 1.0000
3.000 0.1177 0.02915 0.01914 0.0046 1.0000 1.0000
3.250 0.1377 0.02999 0.02003 0.0043 1.0000 1.0000
3.500 0.2964 0.03235 0.02279 -0.0187 0.9211 1.0000
3.750 0.3893 0.03206 0.02287 -0.0272 0.8707 1.0000
4.000 0.4889 0.02945 0.02080 -0.0328 0.8123 1.0000
4.250 0.5676 0.02315 0.01504 -0.0274 0.7057 1.0000
4.500 0.5759 0.02226 0.01195 -0.0161 0.3679 1.0000
4.750 0.5891 0.02426 0.01313 -0.0136 0.3044 1.0000
5.000 0.6145 0.02585 0.01434 -0.0128 0.2696 1.0000
5.250 0.6478 0.02747 0.01561 -0.0131 0.2451 1.0000
5.500 0.6800 0.02905 0.01705 -0.0134 0.2271 1.0000
5.750 0.7094 0.03059 0.01863 -0.0132 0.2134 1.0000
6.000 0.7374 0.03238 0.02056 -0.0130 0.2033 1.0000
6.250 0.7652 0.03440 0.02249 -0.0129 0.1943 1.0000
6.500 0.7887 0.03637 0.02483 -0.0121 0.1877 1.0000
6.750 0.8125 0.03852 0.02723 -0.0115 0.1823 1.0000
7.000 0.8374 0.04122 0.02985 -0.0113 0.1765 1.0000
7.250 0.8550 0.04372 0.03285 -0.0100 0.1737 1.0000
7.500 0.8712 0.04660 0.03619 -0.0088 0.1719 1.0000
7.750 0.8843 0.04967 0.03970 -0.0074 0.1700 1.0000
8.000 0.8943 0.05305 0.04350 -0.0061 0.1688 1.0000
8.250 0.9008 0.05702 0.04788 -0.0047 0.1701 1.0000
8.500 0.9046 0.06131 0.05251 -0.0035 0.1720 1.0000
8.750 0.9075 0.06581 0.05726 -0.0026 0.1737 1.0000
9.000 0.9138 0.07062 0.06222 -0.0021 0.1754 1.0000
9.250 0.8621 0.07821 0.07043 -0.0016 0.1902 1.0000
9.500 0.6154 0.11779 0.11009 -0.0441 0.4243 1.0000
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Polar data table (+)
Polar graphs
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