GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 100,000 Max Cl/Cd: 59.13 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe439-il-100000.txt Download as CSV file: xf-goe439-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3060 0.10477 0.10011 -0.0323 1.0000 0.0611
-8.000 -0.3157 0.10406 0.09952 -0.0325 1.0000 0.0614
-7.750 -0.3241 0.10307 0.09865 -0.0335 1.0000 0.0615
-7.500 -0.3284 0.10165 0.09733 -0.0358 1.0000 0.0617
-7.250 -0.3040 0.09288 0.08853 -0.0280 1.0000 0.0644
-7.000 -0.3074 0.09088 0.08661 -0.0260 1.0000 0.0657
-6.750 -0.3122 0.08903 0.08485 -0.0245 1.0000 0.0672
-6.500 -0.3192 0.08740 0.08332 -0.0231 1.0000 0.0691
-6.250 -0.3281 0.08603 0.08204 -0.0222 1.0000 0.0712
-6.000 -0.3360 0.08466 0.08075 -0.0218 1.0000 0.0722
-5.750 -0.3387 0.08421 0.08030 -0.0284 1.0000 0.0742
-5.500 -0.3371 0.08138 0.07748 -0.0309 1.0000 0.0751
-5.250 -0.3436 0.07809 0.07431 -0.0238 1.0000 0.0766
-5.000 -0.3403 0.07567 0.07191 -0.0220 0.9993 0.0793
-4.750 -0.2761 0.07008 0.06602 -0.0421 0.9899 0.0885
-4.500 -0.2550 0.06559 0.06160 -0.0417 0.9842 0.0916
-4.250 -0.1973 0.06077 0.05644 -0.0561 0.9748 0.1024
-4.000 -0.1714 0.05659 0.05233 -0.0571 0.9688 0.1066
-3.750 -0.1247 0.05216 0.04763 -0.0659 0.9598 0.1179
-3.500 -0.0852 0.04847 0.04376 -0.0712 0.9518 0.1322
-3.250 -0.0439 0.04478 0.03991 -0.0761 0.9443 0.1473
-3.000 -0.0060 0.04154 0.03649 -0.0801 0.9354 0.1621
-2.750 0.0419 0.03832 0.03297 -0.0857 0.9291 0.1888
-2.500 0.1018 0.03134 0.02472 -0.0908 0.9217 0.0993
-2.250 0.1521 0.02714 0.01949 -0.0939 0.9163 0.0874
-2.000 0.1897 0.02524 0.01744 -0.0960 0.9072 0.0960
-1.750 0.2393 0.02303 0.01460 -0.0991 0.9016 0.1033
-1.500 0.2772 0.02184 0.01320 -0.1006 0.8917 0.1170
-1.250 0.3241 0.02037 0.01167 -0.1035 0.8858 0.1368
-1.000 0.3579 0.01935 0.01053 -0.1039 0.8743 0.1578
-0.750 0.3915 0.01819 0.00959 -0.1045 0.8633 0.2018
-0.500 0.4267 0.01713 0.00879 -0.1053 0.8532 0.2670
-0.250 0.4774 0.01464 0.00803 -0.1087 0.8446 1.0000
0.000 0.5079 0.01459 0.00764 -0.1084 0.8310 1.0000
0.250 0.5372 0.01456 0.00737 -0.1079 0.8170 1.0000
0.500 0.5654 0.01457 0.00716 -0.1073 0.8027 1.0000
0.750 0.5930 0.01461 0.00701 -0.1066 0.7881 1.0000
1.000 0.6200 0.01467 0.00691 -0.1059 0.7732 1.0000
1.250 0.6465 0.01477 0.00686 -0.1051 0.7582 1.0000
1.500 0.6728 0.01489 0.00684 -0.1042 0.7432 1.0000
1.750 0.6986 0.01505 0.00686 -0.1034 0.7280 1.0000
2.000 0.7235 0.01524 0.00696 -0.1024 0.7121 1.0000
2.250 0.7485 0.01544 0.00709 -0.1016 0.6965 1.0000
2.500 0.7736 0.01565 0.00721 -0.1007 0.6811 1.0000
2.750 0.7987 0.01586 0.00734 -0.0999 0.6659 1.0000
3.000 0.8239 0.01608 0.00750 -0.0991 0.6510 1.0000
3.250 0.8490 0.01631 0.00770 -0.0983 0.6363 1.0000
3.500 0.8741 0.01656 0.00791 -0.0975 0.6220 1.0000
3.750 0.8992 0.01683 0.00813 -0.0968 0.6078 1.0000
4.000 0.9244 0.01711 0.00839 -0.0961 0.5940 1.0000
4.250 0.9495 0.01743 0.00873 -0.0954 0.5806 1.0000
4.500 0.9746 0.01778 0.00906 -0.0948 0.5675 1.0000
4.750 1.0000 0.01815 0.00942 -0.0941 0.5549 1.0000
5.000 1.0257 0.01855 0.00979 -0.0936 0.5428 1.0000
5.250 1.0498 0.01901 0.01035 -0.0929 0.5300 1.0000
5.500 1.0738 0.01951 0.01095 -0.0922 0.5177 1.0000
5.750 1.0979 0.02004 0.01157 -0.0915 0.5057 1.0000
6.000 1.1216 0.02042 0.01201 -0.0906 0.4916 1.0000
6.250 1.1446 0.02061 0.01219 -0.0894 0.4745 1.0000
6.500 1.1674 0.02074 0.01232 -0.0882 0.4566 1.0000
6.750 1.1864 0.02083 0.01255 -0.0864 0.4356 1.0000
7.000 1.2052 0.02079 0.01250 -0.0844 0.4122 1.0000
7.250 1.2230 0.02089 0.01274 -0.0825 0.3897 1.0000
7.500 1.2376 0.02093 0.01287 -0.0799 0.3591 1.0000
7.750 1.2499 0.02120 0.01319 -0.0770 0.3175 1.0000
8.000 1.2553 0.02218 0.01382 -0.0734 0.2338 1.0000
8.250 1.2421 0.02546 0.01584 -0.0684 0.0889 1.0000
8.500 1.2437 0.02764 0.01788 -0.0649 0.0660 1.0000
8.750 1.2483 0.02929 0.01963 -0.0617 0.0589 1.0000
9.000 1.2499 0.03090 0.02136 -0.0582 0.0549 1.0000
9.250 1.2453 0.03291 0.02345 -0.0545 0.0524 1.0000
9.500 1.2457 0.03470 0.02540 -0.0515 0.0500 1.0000
9.750 1.2453 0.03666 0.02750 -0.0489 0.0479 1.0000
10.000 1.2443 0.03886 0.02976 -0.0466 0.0456 1.0000
10.250 1.2461 0.04110 0.03207 -0.0445 0.0444 1.0000
10.500 1.2585 0.04327 0.03417 -0.0425 0.0431 1.0000
10.750 1.3182 0.04613 0.03691 -0.0433 0.0421 1.0000
11.000 1.3450 0.04879 0.03986 -0.0428 0.0412 1.0000
11.250 1.3631 0.05166 0.04306 -0.0418 0.0403 1.0000
11.500 1.3827 0.05556 0.04731 -0.0410 0.0406 1.0000
11.750 1.3982 0.06023 0.05234 -0.0403 0.0414 1.0000
12.000 1.4169 0.06528 0.05771 -0.0401 0.0427 1.0000
12.250 1.4043 0.06666 0.05945 -0.0360 0.0436 1.0000
12.500 1.3810 0.06959 0.06282 -0.0327 0.0447 1.0000
12.750 1.3561 0.07360 0.06724 -0.0308 0.0457 1.0000
13.000 1.3339 0.07836 0.07233 -0.0302 0.0468 1.0000
13.250 1.3122 0.08352 0.07778 -0.0306 0.0476 1.0000
13.500 1.2905 0.08908 0.08358 -0.0318 0.0484 1.0000
13.750 1.2682 0.09510 0.08982 -0.0339 0.0490 1.0000
14.000 1.2452 0.10159 0.09651 -0.0368 0.0494 1.0000
14.250 1.2215 0.10865 0.10370 -0.0406 0.0498 1.0000
14.500 1.1963 0.11646 0.11168 -0.0455 0.0500 1.0000
14.750 1.1706 0.12515 0.12050 -0.0514 0.0502 1.0000
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Polar data table (+)
Polar graphs
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