GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 50,000 Max Cl/Cd: 32.61 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe375-il-50000.txt Download as CSV file: xf-goe375-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3980 0.11811 0.11121 -0.0071 1.0000 0.0805
-9.000 -0.4008 0.11723 0.11043 -0.0097 1.0000 0.0814
-8.750 -0.4044 0.11627 0.10959 -0.0123 1.0000 0.0818
-8.500 -0.3794 0.10757 0.10083 -0.0088 1.0000 0.0878
-8.250 -0.3750 0.10492 0.09824 -0.0097 1.0000 0.0909
-8.000 -0.3760 0.10307 0.09650 -0.0113 1.0000 0.0941
-7.750 -0.3811 0.10218 0.09573 -0.0149 1.0000 0.0957
-7.500 -0.3737 0.09792 0.09155 -0.0150 1.0000 0.0979
-7.250 -0.3630 0.09379 0.08745 -0.0132 1.0000 0.1038
-7.000 -0.3611 0.09195 0.08569 -0.0172 1.0000 0.1091
-6.750 -0.3561 0.08939 0.08321 -0.0210 1.0000 0.1114
-6.500 -0.3461 0.08496 0.07884 -0.0174 1.0000 0.1191
-6.250 -0.3394 0.08438 0.07822 -0.0256 1.0000 0.1248
-6.000 -0.3321 0.07904 0.07305 -0.0198 1.0000 0.1347
-5.750 -0.3249 0.07599 0.07006 -0.0210 1.0000 0.1439
-5.500 -0.3167 0.07332 0.06742 -0.0228 1.0000 0.1565
-5.250 -0.3096 0.07021 0.06437 -0.0219 1.0000 0.1727
-5.000 -0.3023 0.06732 0.06155 -0.0208 1.0000 0.1908
-4.750 0.0127 0.04126 0.03488 -0.0156 1.0000 1.0000
-4.500 0.0240 0.03936 0.03303 -0.0164 1.0000 1.0000
-4.250 0.0352 0.03751 0.03126 -0.0172 1.0000 1.0000
-4.000 0.0464 0.03576 0.02958 -0.0179 1.0000 1.0000
-3.750 0.0573 0.03407 0.02798 -0.0186 1.0000 1.0000
-3.500 0.0679 0.03246 0.02645 -0.0192 1.0000 1.0000
-3.250 0.0580 0.03202 0.02617 -0.0149 1.0000 0.9910
-3.000 0.0132 0.03323 0.02764 -0.0029 1.0000 0.9622
-2.750 -0.0297 0.03387 0.02854 0.0076 1.0000 0.9338
-2.500 -0.0717 0.03424 0.02918 0.0174 1.0000 0.9136
-2.250 -0.1117 0.03421 0.02942 0.0263 1.0000 0.8962
-2.000 -0.1524 0.03400 0.02945 0.0352 1.0000 0.8852
-1.750 -0.2035 0.03387 0.02954 0.0456 1.0000 0.8731
-1.500 -0.2705 0.03390 0.02983 0.0581 1.0000 0.8568
-1.250 -0.1008 0.03103 0.02529 -0.0125 1.0000 0.5103
-1.000 -0.0236 0.03019 0.02315 -0.0262 1.0000 0.3549
-0.750 0.0157 0.02998 0.02210 -0.0288 1.0000 0.2865
-0.500 0.0422 0.02936 0.02112 -0.0291 1.0000 0.2485
-0.250 0.0724 0.02917 0.02049 -0.0302 0.9974 0.2176
0.000 0.1556 0.02856 0.01913 -0.0392 0.9715 0.1851
0.250 0.2322 0.02761 0.01771 -0.0469 0.9433 0.1695
0.500 0.3114 0.02627 0.01610 -0.0545 0.9151 0.1597
0.750 0.3850 0.02500 0.01474 -0.0610 0.8870 0.1630
1.000 0.4456 0.02394 0.01358 -0.0649 0.8579 0.1649
1.250 0.4957 0.02311 0.01269 -0.0667 0.8271 0.1716
1.500 0.5359 0.02245 0.01209 -0.0667 0.7952 0.1932
1.750 0.5803 0.02048 0.01172 -0.0677 0.7579 1.0000
2.000 0.6069 0.02057 0.01146 -0.0653 0.7234 1.0000
2.250 0.6323 0.02068 0.01122 -0.0630 0.6902 1.0000
2.500 0.6557 0.02094 0.01118 -0.0607 0.6559 1.0000
2.750 0.6798 0.02126 0.01118 -0.0587 0.6240 1.0000
3.000 0.7038 0.02173 0.01135 -0.0569 0.5940 1.0000
3.250 0.7276 0.02234 0.01166 -0.0553 0.5658 1.0000
3.500 0.7517 0.02305 0.01210 -0.0540 0.5407 1.0000
3.750 0.7754 0.02382 0.01265 -0.0527 0.5170 1.0000
4.000 0.7987 0.02472 0.01345 -0.0516 0.4955 1.0000
4.250 0.8219 0.02563 0.01423 -0.0506 0.4753 1.0000
4.500 0.8456 0.02654 0.01501 -0.0496 0.4575 1.0000
4.750 0.8693 0.02751 0.01587 -0.0487 0.4412 1.0000
5.000 0.8926 0.02855 0.01686 -0.0478 0.4258 1.0000
5.250 0.9152 0.02970 0.01808 -0.0470 0.4114 1.0000
5.500 0.9371 0.03090 0.01934 -0.0461 0.3974 1.0000
5.750 0.9580 0.03227 0.02083 -0.0453 0.3846 1.0000
6.000 0.9779 0.03396 0.02270 -0.0446 0.3739 1.0000
6.250 1.0002 0.03543 0.02427 -0.0438 0.3646 1.0000
6.500 1.0196 0.03712 0.02614 -0.0430 0.3547 1.0000
6.750 1.0356 0.03929 0.02857 -0.0422 0.3455 1.0000
7.000 1.0597 0.04059 0.02986 -0.0415 0.3379 1.0000
7.250 1.0667 0.04410 0.03386 -0.0408 0.3318 1.0000
7.500 1.0797 0.04694 0.03695 -0.0402 0.3266 1.0000
7.750 1.0962 0.04941 0.03962 -0.0396 0.3217 1.0000
8.000 1.0851 0.05502 0.04568 -0.0394 0.3178 1.0000
8.250 1.0738 0.06055 0.05147 -0.0395 0.3143 1.0000
8.500 1.0295 0.07013 0.06116 -0.0417 0.3155 1.0000
8.750 0.9830 0.08033 0.07131 -0.0454 0.3205 1.0000
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Polar data table (+)
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