GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 604 AIRFOIL (goe604-il) Reynolds number: 50,000 Max Cl/Cd: 20.58 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe604-il-50000-n5.txt Download as CSV file: xf-goe604-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 604 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2351 0.11439 0.10780 -0.0475 1.0000 0.0836
-11.000 -0.2441 0.11144 0.10497 -0.0473 1.0000 0.0838
-10.750 -0.2574 0.10867 0.10234 -0.0467 1.0000 0.0843
-10.500 -0.2610 0.10438 0.09813 -0.0493 0.9938 0.0846
-10.250 -0.2528 0.09802 0.09177 -0.0559 0.9804 0.0847
-10.000 -0.2501 0.09103 0.08478 -0.0629 0.9660 0.0850
-9.750 -0.2589 0.08221 0.07595 -0.0717 0.9505 0.0856
-9.500 -0.2937 0.06929 0.06291 -0.0850 0.9305 0.0855
-9.250 -0.3296 0.06060 0.05391 -0.0916 0.9073 0.0856
-9.000 -0.3524 0.05411 0.04692 -0.0941 0.8874 0.0862
-8.750 -0.3347 0.05203 0.04477 -0.0946 0.8712 0.0878
-8.500 -0.3251 0.04929 0.04179 -0.0947 0.8548 0.0893
-8.250 -0.3153 0.04672 0.03894 -0.0944 0.8393 0.0915
-8.000 -0.3071 0.04386 0.03563 -0.0937 0.8252 0.0942
-7.750 -0.2933 0.04102 0.03227 -0.0933 0.8136 0.0971
-7.500 -0.2737 0.03996 0.03115 -0.0924 0.7994 0.0996
-7.250 -0.2549 0.03852 0.02948 -0.0915 0.7869 0.1028
-7.000 -0.2339 0.03656 0.02700 -0.0910 0.7772 0.1077
-6.750 -0.2142 0.03589 0.02635 -0.0899 0.7645 0.1114
-6.500 -0.1916 0.03477 0.02498 -0.0891 0.7543 0.1168
-6.250 -0.1697 0.03375 0.02375 -0.0882 0.7438 0.1226
-6.000 -0.1478 0.03304 0.02289 -0.0872 0.7336 0.1300
-5.750 -0.1234 0.03222 0.02193 -0.0866 0.7244 0.1387
-5.500 -0.1017 0.03152 0.02101 -0.0855 0.7145 0.1501
-5.250 -0.0771 0.03088 0.02025 -0.0849 0.7059 0.1636
-5.000 -0.0556 0.03043 0.01978 -0.0838 0.6965 0.1784
-4.750 -0.0316 0.02996 0.01923 -0.0830 0.6879 0.1964
-4.500 -0.0091 0.02967 0.01886 -0.0821 0.6793 0.2149
-4.250 0.0139 0.02944 0.01853 -0.0811 0.6706 0.2340
-4.000 0.0388 0.02922 0.01821 -0.0804 0.6631 0.2537
-3.750 0.0595 0.02918 0.01814 -0.0792 0.6539 0.2726
-3.500 0.0870 0.02893 0.01784 -0.0788 0.6473 0.2948
-3.250 0.1058 0.02898 0.01789 -0.0774 0.6379 0.3136
-3.000 0.1340 0.02871 0.01751 -0.0772 0.6308 0.3330
-2.750 0.1585 0.02860 0.01734 -0.0766 0.6228 0.3504
-2.500 0.1834 0.02846 0.01715 -0.0760 0.6149 0.3691
-2.250 0.2134 0.02810 0.01674 -0.0759 0.6091 0.3923
-2.000 0.2299 0.02825 0.01700 -0.0742 0.6002 0.4145
-1.750 0.2559 0.02803 0.01680 -0.0736 0.5937 0.4452
-1.500 0.2777 0.02793 0.01683 -0.0724 0.5870 0.4818
-1.250 0.2954 0.02795 0.01706 -0.0706 0.5792 0.5274
-1.000 0.3207 0.02763 0.01699 -0.0694 0.5737 0.5978
-0.750 0.3424 0.02767 0.01743 -0.0677 0.5665 0.6929
-0.500 0.4008 0.02777 0.01774 -0.0721 0.5586 0.8399
-0.250 0.4803 0.02785 0.01753 -0.0807 0.5521 0.9405
0.000 0.5426 0.02849 0.01801 -0.0880 0.5427 1.0000
0.250 0.5603 0.02872 0.01801 -0.0865 0.5375 1.0000
0.500 0.5753 0.02914 0.01825 -0.0846 0.5320 1.0000
0.750 0.5820 0.02989 0.01894 -0.0818 0.5250 1.0000
1.000 0.6004 0.03025 0.01912 -0.0803 0.5199 1.0000
1.250 0.6259 0.03041 0.01905 -0.0797 0.5162 1.0000
1.500 0.6227 0.03168 0.02036 -0.0757 0.5086 1.0000
1.750 0.6378 0.03224 0.02081 -0.0738 0.5033 1.0000
2.000 0.6625 0.03246 0.02084 -0.0731 0.4995 1.0000
2.250 0.6637 0.03366 0.02204 -0.0697 0.4932 1.0000
2.500 0.6697 0.03469 0.02302 -0.0669 0.4872 1.0000
2.750 0.6908 0.03512 0.02333 -0.0658 0.4833 1.0000
3.000 0.7192 0.03532 0.02337 -0.0657 0.4805 1.0000
3.250 0.6908 0.03800 0.02619 -0.0593 0.4724 1.0000
3.500 0.7007 0.03901 0.02714 -0.0573 0.4678 1.0000
3.750 0.7268 0.03930 0.02731 -0.0568 0.4647 1.0000
4.000 0.6941 0.04237 0.03045 -0.0507 0.4572 1.0000
4.250 0.6780 0.04485 0.03294 -0.0467 0.4508 1.0000
4.500 0.6992 0.04547 0.03347 -0.0459 0.4479 1.0000
4.750 0.7287 0.04565 0.03356 -0.0458 0.4459 1.0000
5.250 0.6629 0.05504 0.04307 -0.0396 0.4299 1.0000
6.250 0.6026 0.07273 0.06084 -0.0374 0.4038 1.0000
6.500 0.6117 0.07478 0.06287 -0.0370 0.3999 1.0000
6.750 0.6288 0.07612 0.06418 -0.0367 0.3974 1.0000
7.000 0.6508 0.07698 0.06500 -0.0362 0.3955 1.0000
7.250 0.6166 0.08342 0.07150 -0.0364 0.3868 1.0000
7.500 0.6286 0.08520 0.07327 -0.0361 0.3828 1.0000
7.750 0.6526 0.08574 0.07378 -0.0356 0.3800 1.0000
8.000 0.6397 0.08976 0.07783 -0.0355 0.3715 1.0000
8.250 0.6560 0.09077 0.07883 -0.0350 0.3659 1.0000
8.500 0.6860 0.09043 0.07845 -0.0342 0.3627 1.0000
8.750 0.6685 0.09493 0.08300 -0.0344 0.3524 1.0000
9.000 0.6891 0.09556 0.08361 -0.0339 0.3481 1.0000
9.250 0.7179 0.09531 0.08333 -0.0331 0.3454 1.0000
9.500 0.6940 0.10087 0.08897 -0.0339 0.3346 1.0000
9.750 0.7153 0.10146 0.08957 -0.0334 0.3308 1.0000
10.250 0.7191 0.10702 0.09519 -0.0336 0.3166 1.0000
10.500 0.7426 0.10726 0.09543 -0.0330 0.3133 1.0000
11.000 0.7424 0.11365 0.10191 -0.0337 0.2988 1.0000
11.250 0.7655 0.11398 0.10224 -0.0332 0.2962 1.0000
11.500 0.7455 0.11981 0.10814 -0.0346 0.2852 1.0000
11.750 0.7643 0.12064 0.10898 -0.0343 0.2817 1.0000
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