GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 50,000 Max Cl/Cd: 26.58 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe426-il-50000-n5.txt Download as CSV file: xf-goe426-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2596 0.11000 0.10329 -0.0410 1.0000 0.1531
-9.000 -0.2842 0.10981 0.10330 -0.0409 1.0000 0.1579
-8.750 -0.3152 0.11001 0.10372 -0.0396 1.0000 0.1588
-8.500 -0.3169 0.10736 0.10119 -0.0371 1.0000 0.1597
-8.250 -0.3008 0.10370 0.09754 -0.0364 0.9969 0.1617
-7.750 -0.2826 0.08854 0.08220 -0.0558 0.9678 0.0926
-7.500 -0.2852 0.07831 0.07184 -0.0721 0.9481 0.0819
-7.250 -0.2662 0.07386 0.06729 -0.0765 0.9366 0.0809
-7.000 -0.2482 0.06890 0.06219 -0.0823 0.9255 0.0805
-6.750 -0.2313 0.06422 0.05733 -0.0872 0.9137 0.0800
-6.500 -0.2173 0.06014 0.05306 -0.0905 0.9002 0.0793
-6.250 -0.2015 0.05625 0.04893 -0.0933 0.8876 0.0782
-6.000 -0.1818 0.05224 0.04457 -0.0964 0.8771 0.0771
-5.750 -0.1630 0.04874 0.04070 -0.0983 0.8654 0.0763
-5.500 -0.1443 0.04574 0.03729 -0.0993 0.8533 0.0757
-5.250 -0.1200 0.04288 0.03399 -0.1007 0.8436 0.0754
-5.000 -0.0956 0.04062 0.03133 -0.1014 0.8333 0.0762
-4.750 -0.0724 0.03877 0.02908 -0.1015 0.8224 0.0777
-4.500 -0.0421 0.03678 0.02664 -0.1024 0.8148 0.0791
-4.250 -0.0190 0.03531 0.02481 -0.1020 0.8035 0.0798
-4.000 0.0096 0.03381 0.02293 -0.1021 0.7951 0.0803
-3.750 0.0367 0.03257 0.02138 -0.1019 0.7858 0.0810
-3.500 0.0642 0.03147 0.02005 -0.1017 0.7770 0.0820
-3.250 0.0921 0.03045 0.01895 -0.1016 0.7688 0.0840
-3.000 0.1179 0.02976 0.01818 -0.1012 0.7599 0.0873
-2.750 0.1462 0.02906 0.01732 -0.1009 0.7521 0.0913
-2.500 0.1720 0.02855 0.01660 -0.1002 0.7437 0.0943
-2.250 0.1990 0.02789 0.01591 -0.0999 0.7361 0.0975
-2.000 0.2248 0.02744 0.01537 -0.0995 0.7283 0.1019
-1.750 0.2504 0.02713 0.01489 -0.0990 0.7203 0.1094
-1.500 0.2782 0.02660 0.01434 -0.0990 0.7140 0.1213
-1.250 0.3010 0.02631 0.01409 -0.0985 0.7054 0.1382
-1.000 0.3282 0.02476 0.01361 -0.0991 0.6999 0.3224
-0.750 0.3382 0.02422 0.01421 -0.0953 0.6916 0.6272
-0.500 0.3531 0.02388 0.01431 -0.0909 0.6855 0.7907
-0.250 0.4133 0.02351 0.01392 -0.0957 0.6793 1.0000
0.000 0.4343 0.02391 0.01406 -0.0951 0.6713 1.0000
0.250 0.4633 0.02405 0.01388 -0.0953 0.6662 1.0000
0.500 0.4817 0.02465 0.01431 -0.0945 0.6577 1.0000
0.750 0.5089 0.02489 0.01431 -0.0944 0.6518 1.0000
1.000 0.5319 0.02535 0.01460 -0.0940 0.6451 1.0000
1.250 0.5547 0.02581 0.01491 -0.0935 0.6381 1.0000
1.500 0.5848 0.02594 0.01484 -0.0937 0.6333 1.0000
1.750 0.6014 0.02675 0.01558 -0.0926 0.6250 1.0000
2.000 0.6285 0.02703 0.01572 -0.0924 0.6195 1.0000
2.250 0.6514 0.02754 0.01613 -0.0919 0.6132 1.0000
2.500 0.6720 0.02818 0.01671 -0.0912 0.6062 1.0000
2.750 0.7020 0.02834 0.01674 -0.0913 0.6017 1.0000
3.000 0.7169 0.02929 0.01769 -0.0900 0.5937 1.0000
3.250 0.7423 0.02970 0.01803 -0.0897 0.5881 1.0000
3.500 0.7712 0.02995 0.01819 -0.0897 0.5836 1.0000
3.750 0.7826 0.03113 0.01942 -0.0881 0.5751 1.0000
4.000 0.8114 0.03137 0.01960 -0.0881 0.5705 1.0000
4.250 0.8264 0.03241 0.02067 -0.0869 0.5634 1.0000
4.500 0.8463 0.03315 0.02142 -0.0861 0.5570 1.0000
4.750 0.8781 0.03325 0.02148 -0.0863 0.5531 1.0000
5.000 0.8816 0.03498 0.02330 -0.0841 0.5442 1.0000
5.250 0.9070 0.03544 0.02376 -0.0838 0.5392 1.0000
5.500 0.9413 0.03542 0.02373 -0.0842 0.5359 1.0000
5.750 0.9328 0.03789 0.02633 -0.0811 0.5255 1.0000
6.000 0.9625 0.03812 0.02658 -0.0811 0.5214 1.0000
6.500 0.9770 0.04131 0.02993 -0.0776 0.5069 1.0000
6.750 1.0114 0.04127 0.02993 -0.0779 0.5037 1.0000
7.000 0.9793 0.04532 0.03407 -0.0734 0.4919 1.0000
7.250 1.0106 0.04541 0.03423 -0.0734 0.4883 1.0000
7.750 1.0022 0.05065 0.03960 -0.0695 0.4724 1.0000
8.000 1.0378 0.05031 0.03936 -0.0695 0.4700 1.0000
8.500 0.9675 0.06270 0.05187 -0.0668 0.4435 1.0000
8.750 0.9922 0.06310 0.05236 -0.0662 0.4402 1.0000
9.250 0.9906 0.06949 0.05891 -0.0654 0.4248 1.0000
9.750 0.9911 0.07576 0.06536 -0.0649 0.4100 1.0000
10.000 1.0203 0.07563 0.06538 -0.0641 0.4073 1.0000
10.250 0.9943 0.08182 0.07163 -0.0646 0.3955 1.0000
10.500 1.0230 0.08165 0.07161 -0.0637 0.3924 1.0000
10.750 1.0029 0.08718 0.07721 -0.0642 0.3809 1.0000
11.000 1.0359 0.08618 0.07637 -0.0630 0.3771 1.0000
11.250 1.0214 0.09089 0.08116 -0.0633 0.3650 1.0000
11.500 1.0593 0.08888 0.07935 -0.0617 0.3612 1.0000
11.750 1.0442 0.09379 0.08434 -0.0622 0.3488 1.0000
12.000 1.0389 0.09760 0.08826 -0.0625 0.3384 1.0000
12.250 1.0643 0.09716 0.08800 -0.0614 0.3328 1.0000
12.750 1.0847 0.10039 0.09157 -0.0605 0.3165 1.0000
13.000 1.0736 0.10514 0.09641 -0.0614 0.3040 1.0000
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Polar data table (+)
Polar graphs
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