GOE 451 AIRFOIL (modified line 6) (goe451-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 451 AIRFOIL (modified line 6) (goe451-il) Reynolds number: 50,000 Max Cl/Cd: 36.5 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe451-il-50000.txt Download as CSV file: xf-goe451-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 451 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4351 0.10936 0.10235 -0.0218 1.0000 0.0809
-8.000 -0.4388 0.10882 0.10194 -0.0231 1.0000 0.0822
-7.750 -0.4382 0.10842 0.10164 -0.0267 1.0000 0.0828
-7.500 -0.4274 0.10062 0.09391 -0.0230 1.0000 0.0863
-7.250 -0.4220 0.09747 0.09084 -0.0233 1.0000 0.0904
-7.000 -0.4176 0.09542 0.08888 -0.0258 1.0000 0.0943
-6.750 -0.4093 0.09519 0.08871 -0.0326 1.0000 0.0962
-6.500 -0.4044 0.08883 0.08246 -0.0281 1.0000 0.1003
-6.250 -0.3959 0.08594 0.07962 -0.0296 1.0000 0.1066
-6.000 -0.3815 0.08411 0.07783 -0.0364 1.0000 0.1106
-5.750 -0.3769 0.07941 0.07322 -0.0327 1.0000 0.1173
-5.500 -0.3596 0.07697 0.07064 -0.0386 1.0000 0.1245
-5.250 -0.3473 0.07365 0.06735 -0.0396 1.0000 0.1354
-5.000 -0.3381 0.06968 0.06347 -0.0389 1.0000 0.1427
-4.750 -0.3220 0.06633 0.06014 -0.0414 1.0000 0.1548
-4.500 -0.3061 0.06301 0.05683 -0.0431 1.0000 0.1692
-4.250 -0.2824 0.06009 0.05385 -0.0478 1.0000 0.1914
-4.000 -0.2725 0.05637 0.05022 -0.0462 1.0000 0.2123
-3.750 -0.2558 0.05319 0.04706 -0.0474 1.0000 0.2474
-2.000 0.0016 0.02986 0.02165 -0.0762 1.0000 0.1854
-1.750 0.0394 0.02717 0.01818 -0.0780 1.0000 0.1726
-1.500 0.0747 0.02476 0.01511 -0.0790 1.0000 0.1591
-1.250 0.1069 0.02296 0.01257 -0.0792 1.0000 0.1498
-1.000 0.1347 0.02150 0.01068 -0.0789 1.0000 0.1486
-0.750 0.1616 0.02046 0.00924 -0.0783 1.0000 0.1508
-0.500 0.1866 0.01957 0.00821 -0.0778 1.0000 0.1602
-0.250 0.2107 0.01890 0.00754 -0.0775 1.0000 0.1909
0.000 0.2376 0.01668 0.00708 -0.0780 1.0000 0.5733
0.250 0.2527 0.01652 0.00666 -0.0757 1.0000 1.0000
0.500 0.2726 0.01686 0.00673 -0.0750 1.0000 1.0000
0.750 0.3016 0.01728 0.00695 -0.0764 0.9948 1.0000
1.000 0.3751 0.01737 0.00692 -0.0865 0.9601 1.0000
1.250 0.4669 0.01583 0.00518 -0.0970 0.8742 1.0000
1.500 0.5022 0.01559 0.00481 -0.0982 0.8301 1.0000
1.750 0.5371 0.01545 0.00436 -0.0989 0.7631 1.0000
2.000 0.5638 0.01562 0.00421 -0.0983 0.6932 1.0000
2.250 0.5855 0.01604 0.00418 -0.0970 0.5849 1.0000
2.500 0.5886 0.01931 0.00483 -0.0934 0.0947 1.0000
2.750 0.6091 0.02033 0.00607 -0.0928 0.0796 1.0000
3.000 0.6277 0.02187 0.00782 -0.0922 0.0666 1.0000
3.250 0.6425 0.02392 0.00999 -0.0912 0.0547 1.0000
3.500 0.6586 0.02614 0.01219 -0.0902 0.0421 1.0000
3.750 0.7001 0.03062 0.01580 -0.0929 0.0307 1.0000
4.000 0.7213 0.03112 0.01666 -0.0922 0.0246 1.0000
4.250 0.7484 0.03291 0.01847 -0.0925 0.0219 1.0000
4.500 0.7716 0.03384 0.01967 -0.0919 0.0191 1.0000
4.750 0.8000 0.03760 0.02336 -0.0928 0.0167 1.0000
5.000 0.8256 0.04130 0.02736 -0.0930 0.0158 1.0000
5.250 0.8448 0.04033 0.02701 -0.0912 0.0151 1.0000
5.500 0.8665 0.04143 0.02849 -0.0903 0.0142 1.0000
5.750 0.8883 0.04323 0.03065 -0.0896 0.0135 1.0000
6.000 0.9091 0.04541 0.03323 -0.0889 0.0127 1.0000
6.250 0.9286 0.04821 0.03648 -0.0882 0.0119 1.0000
6.500 0.9465 0.05235 0.04105 -0.0878 0.0113 1.0000
6.750 0.9646 0.06055 0.04944 -0.0888 0.0108 1.0000
8.500 1.0582 0.07036 0.06198 -0.0802 0.0091 1.0000
8.750 1.0665 0.07361 0.06558 -0.0789 0.0090 1.0000
9.000 1.0730 0.07704 0.06933 -0.0776 0.0088 1.0000
9.250 1.0775 0.08060 0.07319 -0.0763 0.0087 1.0000
9.500 1.0799 0.08426 0.07713 -0.0750 0.0086 1.0000
9.750 1.0801 0.08797 0.08111 -0.0738 0.0085 1.0000
10.000 1.0780 0.09172 0.08509 -0.0727 0.0085 1.0000
10.250 1.0735 0.09546 0.08904 -0.0716 0.0085 1.0000
10.500 1.0665 0.09917 0.09293 -0.0707 0.0085 1.0000
10.750 1.0561 0.10270 0.09660 -0.0696 0.0085 1.0000
11.000 1.0440 0.10631 0.10034 -0.0690 0.0085 1.0000
11.250 1.0319 0.11030 0.10443 -0.0695 0.0086 1.0000
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Polar data table (+)
Polar graphs
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