GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 50,000 Max Cl/Cd: 34.78 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe364-il-50000-n5.txt Download as CSV file: xf-goe364-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 364 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2227 0.11705 0.11085 -0.0316 1.0000 0.0824
-8.750 -0.2308 0.11594 0.10987 -0.0295 1.0000 0.0840
-8.500 -0.2425 0.11526 0.10933 -0.0271 1.0000 0.0853
-8.250 -0.2461 0.11398 0.10814 -0.0276 0.9967 0.0873
-8.000 -0.2385 0.11268 0.10686 -0.0357 0.9835 0.0897
-7.750 -0.2313 0.11138 0.10557 -0.0453 0.9670 0.0903
-7.500 -0.1997 0.10339 0.09758 -0.0409 0.9676 0.0940
-7.250 -0.1820 0.10004 0.09423 -0.0443 0.9583 0.0992
-7.000 -0.1724 0.09825 0.09244 -0.0525 0.9425 0.1039
-6.750 -0.1554 0.09450 0.08869 -0.0585 0.9317 0.1060
-6.500 -0.1377 0.09015 0.08435 -0.0566 0.9234 0.1099
-6.250 -0.1142 0.08655 0.08071 -0.0617 0.9147 0.1156
-6.000 -0.0949 0.08494 0.07894 -0.0740 0.8991 0.1207
-5.500 -0.0555 0.07660 0.07062 -0.0738 0.8821 0.1326
-5.250 -0.0369 0.07337 0.06732 -0.0779 0.8707 0.1393
-5.000 -0.0190 0.07046 0.06439 -0.0785 0.8606 0.1470
-4.500 0.0272 0.06485 0.05852 -0.0858 0.8415 0.1678
-4.250 0.0501 0.06130 0.05493 -0.0871 0.8344 0.1750
-4.000 0.0690 0.05886 0.05243 -0.0882 0.8244 0.1914
-3.750 0.0898 0.05639 0.04990 -0.0888 0.8159 0.2111
-3.250 0.1818 0.04734 0.03953 -0.1012 0.7996 0.0874
-3.000 0.2090 0.04495 0.03689 -0.1022 0.7908 0.0858
-2.750 0.2378 0.04274 0.03437 -0.1031 0.7826 0.0850
-2.500 0.2660 0.04064 0.03192 -0.1036 0.7738 0.0826
-2.250 0.2967 0.03858 0.02938 -0.1042 0.7658 0.0797
-2.000 0.3259 0.03693 0.02723 -0.1041 0.7569 0.0778
-1.750 0.3536 0.03557 0.02564 -0.1041 0.7485 0.0790
-1.500 0.3810 0.03444 0.02426 -0.1039 0.7395 0.0807
-1.250 0.4087 0.03337 0.02289 -0.1036 0.7308 0.0812
-1.000 0.4382 0.03234 0.02154 -0.1034 0.7222 0.0811
-0.750 0.4657 0.03156 0.02049 -0.1029 0.7130 0.0815
-0.500 0.4960 0.03075 0.01942 -0.1028 0.7048 0.0826
-0.250 0.5209 0.03034 0.01882 -0.1019 0.6952 0.0854
0.000 0.5552 0.02973 0.01790 -0.1023 0.6875 0.0888
0.250 0.5810 0.02949 0.01748 -0.1016 0.6775 0.0906
0.500 0.6138 0.02888 0.01676 -0.1019 0.6702 0.0936
0.750 0.6356 0.02887 0.01668 -0.1008 0.6600 0.0971
1.000 0.6673 0.02850 0.01612 -0.1008 0.6531 0.1045
1.250 0.6870 0.02862 0.01629 -0.0995 0.6427 0.1138
1.500 0.7191 0.02823 0.01583 -0.0997 0.6362 0.1297
1.750 0.7386 0.02833 0.01616 -0.0986 0.6258 0.1710
2.000 0.7849 0.02647 0.01567 -0.1014 0.6193 1.0000
2.250 0.8015 0.02713 0.01615 -0.0996 0.6085 1.0000
2.500 0.8292 0.02725 0.01601 -0.0991 0.6002 1.0000
2.750 0.8501 0.02759 0.01619 -0.0977 0.5893 1.0000
3.000 0.8705 0.02795 0.01642 -0.0963 0.5785 1.0000
3.250 0.9003 0.02788 0.01614 -0.0959 0.5701 1.0000
3.500 0.9160 0.02847 0.01668 -0.0940 0.5586 1.0000
3.750 0.9397 0.02873 0.01683 -0.0931 0.5497 1.0000
4.000 0.9618 0.02908 0.01709 -0.0919 0.5404 1.0000
4.250 0.9808 0.02961 0.01758 -0.0905 0.5311 1.0000
4.500 1.0067 0.02979 0.01766 -0.0899 0.5231 1.0000
4.750 1.0225 0.03049 0.01837 -0.0882 0.5133 1.0000
5.000 1.0516 0.03051 0.01828 -0.0879 0.5058 1.0000
5.250 1.0643 0.03136 0.01917 -0.0858 0.4955 1.0000
5.500 1.0905 0.03155 0.01930 -0.0853 0.4877 1.0000
5.750 1.1062 0.03224 0.02002 -0.0835 0.4777 1.0000
6.000 1.1265 0.03273 0.02050 -0.0824 0.4690 1.0000
6.250 1.1477 0.03318 0.02095 -0.0813 0.4599 1.0000
6.500 1.1628 0.03396 0.02177 -0.0795 0.4505 1.0000
6.750 1.1886 0.03420 0.02196 -0.0790 0.4420 1.0000
7.000 1.1979 0.03526 0.02311 -0.0766 0.4319 1.0000
7.250 1.2286 0.03532 0.02311 -0.0766 0.4241 1.0000
7.500 1.2310 0.03674 0.02466 -0.0736 0.4137 1.0000
7.750 1.2557 0.03712 0.02501 -0.0730 0.4058 1.0000
8.000 1.2598 0.03844 0.02645 -0.0703 0.3961 1.0000
8.250 1.2778 0.03912 0.02717 -0.0690 0.3881 1.0000
8.500 1.2818 0.04044 0.02859 -0.0662 0.3792 1.0000
8.750 1.2960 0.04134 0.02953 -0.0646 0.3716 1.0000
9.000 1.2975 0.04292 0.03122 -0.0620 0.3633 1.0000
9.250 1.3128 0.04378 0.03215 -0.0606 0.3563 1.0000
9.500 1.3065 0.04596 0.03447 -0.0578 0.3481 1.0000
9.750 1.3285 0.04640 0.03492 -0.0570 0.3417 1.0000
10.000 1.3070 0.04994 0.03865 -0.0539 0.3339 1.0000
10.250 1.3409 0.04936 0.03805 -0.0535 0.3279 1.0000
10.500 1.2993 0.05503 0.04395 -0.0506 0.3198 1.0000
10.750 1.3264 0.05480 0.04377 -0.0498 0.3140 1.0000
11.000 1.2809 0.06191 0.05105 -0.0485 0.3059 1.0000
11.250 1.2993 0.06239 0.05162 -0.0475 0.3000 1.0000
11.500 1.2367 0.07308 0.06245 -0.0483 0.2903 1.0000
11.750 1.2577 0.07311 0.06257 -0.0473 0.2853 1.0000
12.000 1.1846 0.08724 0.07679 -0.0507 0.2732 1.0000
12.250 1.2154 0.08552 0.07517 -0.0489 0.2697 1.0000
12.500 1.2680 0.08066 0.07038 -0.0462 0.2675 1.0000
12.750 1.1768 0.09873 0.08854 -0.0519 0.2538 1.0000
13.000 1.2182 0.09495 0.08486 -0.0492 0.2519 1.0000
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