GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.37 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe441-il-1000000.txt Download as CSV file: xf-goe441-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0241 0.10697 0.10444 -0.0892 0.8126 0.0298
-11.000 -0.0120 0.10499 0.10243 -0.0897 0.8020 0.0300
-10.750 -0.2961 0.02546 0.02190 -0.1737 0.8006 0.0291
-10.500 -0.2662 0.02302 0.01919 -0.1793 0.7918 0.0293
-10.250 -0.2369 0.02150 0.01747 -0.1823 0.7832 0.0295
-10.000 -0.2080 0.02044 0.01621 -0.1844 0.7752 0.0296
-9.750 -0.1795 0.01811 0.01364 -0.1877 0.7684 0.0300
-9.500 -0.1507 0.01703 0.01244 -0.1891 0.7614 0.0303
-9.250 -0.1214 0.01635 0.01167 -0.1902 0.7552 0.0306
-9.000 -0.0919 0.01580 0.01107 -0.1910 0.7482 0.0310
-8.750 -0.0627 0.01533 0.01049 -0.1917 0.7407 0.0313
-8.500 -0.0329 0.01480 0.00988 -0.1925 0.7339 0.0317
-8.250 -0.0033 0.01429 0.00927 -0.1932 0.7254 0.0320
-8.000 0.0264 0.01383 0.00870 -0.1938 0.7174 0.0323
-7.750 0.0563 0.01339 0.00817 -0.1945 0.7092 0.0326
-7.500 0.0858 0.01301 0.00768 -0.1950 0.7001 0.0330
-7.250 0.1158 0.01265 0.00724 -0.1955 0.6896 0.0333
-7.000 0.1453 0.01238 0.00686 -0.1958 0.6763 0.0336
-6.750 0.1746 0.01198 0.00632 -0.1963 0.6560 0.0339
-6.500 0.2023 0.01166 0.00578 -0.1966 0.6105 0.0346
-6.250 0.2279 0.01174 0.00555 -0.1963 0.5534 0.0351
-6.000 0.2563 0.01167 0.00535 -0.1964 0.5337 0.0357
-5.750 0.2851 0.01158 0.00515 -0.1967 0.5218 0.0363
-5.500 0.3148 0.01144 0.00495 -0.1970 0.5145 0.0370
-5.250 0.3441 0.01134 0.00477 -0.1973 0.5077 0.0377
-5.000 0.3732 0.01127 0.00461 -0.1975 0.5006 0.0383
-4.750 0.4038 0.01098 0.00431 -0.1981 0.4967 0.0396
-4.500 0.4336 0.01086 0.00415 -0.1984 0.4923 0.0407
-4.250 0.4631 0.01079 0.00403 -0.1987 0.4879 0.0419
-4.000 0.4921 0.01077 0.00394 -0.1988 0.4829 0.0430
-3.750 0.5224 0.01059 0.00376 -0.1993 0.4798 0.0452
-3.500 0.5523 0.01049 0.00365 -0.1996 0.4770 0.0475
-3.250 0.5823 0.01038 0.00353 -0.2000 0.4736 0.0508
-3.000 0.6118 0.01032 0.00344 -0.2002 0.4699 0.0552
-2.750 0.6409 0.01028 0.00339 -0.2004 0.4659 0.0625
-2.500 0.6698 0.01028 0.00341 -0.2006 0.4620 0.0728
-2.250 0.6994 0.01025 0.00343 -0.2009 0.4601 0.0824
-2.000 0.7288 0.01025 0.00345 -0.2010 0.4577 0.0890
-1.750 0.7577 0.01030 0.00348 -0.2011 0.4548 0.0939
-1.500 0.7867 0.01030 0.00348 -0.2013 0.4516 0.0987
-1.250 0.8152 0.01036 0.00351 -0.2014 0.4482 0.1030
-1.000 0.8430 0.01049 0.00359 -0.2013 0.4443 0.1060
-0.750 0.8723 0.01045 0.00357 -0.2015 0.4423 0.1109
-0.500 0.9016 0.01044 0.00357 -0.2018 0.4402 0.1150
-0.250 0.9305 0.01046 0.00358 -0.2019 0.4377 0.1184
0.000 0.9593 0.01046 0.00359 -0.2021 0.4349 0.1244
0.250 0.9878 0.01050 0.00362 -0.2022 0.4321 0.1306
0.500 1.0158 0.01056 0.00368 -0.2022 0.4290 0.1388
0.750 1.0435 0.01064 0.00380 -0.2022 0.4252 0.1636
1.000 1.0727 0.01061 0.00387 -0.2025 0.4235 0.2003
1.250 1.1015 0.01061 0.00393 -0.2027 0.4214 0.2233
1.500 1.1300 0.01062 0.00399 -0.2028 0.4189 0.2449
1.750 1.1583 0.01063 0.00408 -0.2030 0.4161 0.2804
2.000 1.1866 0.01061 0.00422 -0.2032 0.4131 0.3657
2.250 1.2135 0.01073 0.00439 -0.2031 0.4095 0.4134
2.500 1.2407 0.01082 0.00454 -0.2030 0.4067 0.4439
2.750 1.2687 0.01087 0.00464 -0.2031 0.4047 0.4650
3.000 1.2964 0.01094 0.00474 -0.2030 0.4022 0.4828
3.250 1.3235 0.01104 0.00486 -0.2029 0.3995 0.4993
3.500 1.3501 0.01116 0.00499 -0.2027 0.3967 0.5168
3.750 1.3759 0.01131 0.00515 -0.2024 0.3935 0.5367
4.000 1.4013 0.01148 0.00536 -0.2020 0.3901 0.5621
4.250 1.4286 0.01153 0.00550 -0.2020 0.3886 0.5947
4.500 1.4558 0.01156 0.00568 -0.2020 0.3865 0.6519
4.750 1.4824 0.01156 0.00589 -0.2019 0.3841 0.7541
5.000 1.5024 0.01135 0.00602 -0.2003 0.3815 1.0000
5.250 1.5271 0.01155 0.00619 -0.1998 0.3785 1.0000
5.500 1.5505 0.01180 0.00640 -0.1991 0.3750 1.0000
5.750 1.5748 0.01201 0.00660 -0.1985 0.3725 1.0000
6.000 1.6000 0.01215 0.00676 -0.1981 0.3706 1.0000
6.250 1.6237 0.01231 0.00693 -0.1974 0.3682 1.0000
6.500 1.6463 0.01250 0.00713 -0.1966 0.3656 1.0000
6.750 1.6682 0.01274 0.00736 -0.1956 0.3628 1.0000
7.000 1.6890 0.01303 0.00763 -0.1945 0.3596 1.0000
7.250 1.7095 0.01335 0.00794 -0.1933 0.3564 1.0000
7.500 1.7333 0.01352 0.00814 -0.1927 0.3539 1.0000
7.750 1.7557 0.01374 0.00838 -0.1919 0.3500 1.0000
8.000 1.7760 0.01406 0.00868 -0.1908 0.3454 1.0000
8.250 1.7941 0.01449 0.00908 -0.1894 0.3403 1.0000
8.500 1.8170 0.01471 0.00933 -0.1887 0.3368 1.0000
8.750 1.8375 0.01504 0.00966 -0.1877 0.3323 1.0000
9.000 1.8553 0.01550 0.01010 -0.1863 0.3271 1.0000
9.250 1.8748 0.01589 0.01050 -0.1852 0.3222 1.0000
9.500 1.8944 0.01628 0.01091 -0.1842 0.3174 1.0000
9.750 1.9112 0.01682 0.01143 -0.1827 0.3118 1.0000
10.000 1.9287 0.01733 0.01195 -0.1814 0.3069 1.0000
10.250 1.9466 0.01783 0.01246 -0.1802 0.3012 1.0000
10.500 1.9602 0.01859 0.01318 -0.1784 0.2941 1.0000
10.750 1.9775 0.01914 0.01376 -0.1772 0.2888 1.0000
11.000 1.9913 0.01991 0.01452 -0.1756 0.2817 1.0000
11.250 2.0043 0.02075 0.01534 -0.1739 0.2744 1.0000
11.500 2.0149 0.02175 0.01632 -0.1720 0.2655 1.0000
11.750 2.0265 0.02272 0.01729 -0.1702 0.2576 1.0000
12.000 2.0330 0.02405 0.01858 -0.1680 0.2483 1.0000
12.250 2.0427 0.02520 0.01972 -0.1662 0.2395 1.0000
12.500 2.0480 0.02669 0.02119 -0.1640 0.2304 1.0000
12.750 2.0489 0.02855 0.02301 -0.1616 0.2193 1.0000
13.000 2.0493 0.03052 0.02495 -0.1592 0.2074 1.0000
13.250 2.0451 0.03295 0.02733 -0.1566 0.1937 1.0000
13.500 2.0355 0.03597 0.03028 -0.1538 0.1782 1.0000
13.750 2.0182 0.03982 0.03405 -0.1507 0.1579 1.0000
14.000 1.9911 0.04487 0.03902 -0.1475 0.1371 1.0000
14.250 1.9625 0.05036 0.04447 -0.1448 0.1200 1.0000
14.500 1.9359 0.05598 0.05008 -0.1426 0.1072 1.0000
14.750 1.9076 0.06209 0.05623 -0.1410 0.0955 1.0000
15.000 1.8728 0.06938 0.06353 -0.1397 0.0787 1.0000
15.250 1.8375 0.07706 0.07124 -0.1390 0.0637 1.0000
15.500 1.8027 0.08487 0.07910 -0.1387 0.0527 1.0000
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