GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 50,000 Max Cl/Cd: 44.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417-il-50000-n5.txt Download as CSV file: xf-goe417-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2793 0.10622 0.09992 -0.0228 1.0000 0.0558
-7.250 -0.2859 0.10501 0.09882 -0.0210 1.0000 0.0569
-7.000 -0.2919 0.10385 0.09776 -0.0197 1.0000 0.0581
-6.750 -0.2964 0.10289 0.09690 -0.0196 1.0000 0.0593
-6.500 -0.2990 0.10222 0.09632 -0.0207 1.0000 0.0601
-6.250 -0.2978 0.10163 0.09579 -0.0233 1.0000 0.0607
-6.000 -0.2915 0.10071 0.09490 -0.0269 1.0000 0.0610
-5.750 -0.2934 0.09511 0.08939 -0.0218 1.0000 0.0621
-5.500 -0.2929 0.09139 0.08574 -0.0184 1.0000 0.0643
-5.250 -0.2895 0.08891 0.08330 -0.0179 1.0000 0.0670
-5.000 -0.2830 0.08675 0.08117 -0.0191 1.0000 0.0711
-4.750 -0.2533 0.08697 0.08126 -0.0306 1.0000 0.0753
-4.500 -0.2486 0.08095 0.07537 -0.0271 0.9962 0.0779
-4.250 -0.2220 0.07710 0.07148 -0.0309 0.9899 0.0843
-4.000 -0.1709 0.07380 0.06800 -0.0436 0.9823 0.0912
-3.750 -0.1501 0.06948 0.06368 -0.0445 0.9766 0.0971
-3.500 -0.1102 0.06604 0.06010 -0.0522 0.9689 0.1075
-3.250 -0.0717 0.06273 0.05666 -0.0585 0.9619 0.1214
-3.000 -0.0328 0.05949 0.05329 -0.0645 0.9547 0.1356
-2.750 0.0042 0.05641 0.05006 -0.0694 0.9473 0.1504
-2.500 0.0375 0.05314 0.04671 -0.0728 0.9401 0.1676
-1.500 0.2344 0.04072 0.03280 -0.0955 0.9102 0.0999
-1.250 0.2793 0.03808 0.02967 -0.0988 0.8998 0.0867
-1.000 0.3247 0.03563 0.02681 -0.1022 0.8900 0.0810
-0.750 0.3737 0.03338 0.02396 -0.1055 0.8807 0.0775
-0.500 0.4105 0.03190 0.02223 -0.1071 0.8684 0.0811
-0.250 0.4487 0.03045 0.02041 -0.1085 0.8568 0.0810
0.000 0.4870 0.02912 0.01869 -0.1098 0.8462 0.0798
0.250 0.5288 0.02782 0.01701 -0.1114 0.8376 0.0794
0.500 0.5629 0.02696 0.01581 -0.1118 0.8250 0.0798
0.750 0.5964 0.02619 0.01480 -0.1120 0.8121 0.0807
1.000 0.6291 0.02549 0.01394 -0.1121 0.7988 0.0837
1.250 0.6607 0.02494 0.01321 -0.1120 0.7848 0.0899
1.500 0.6917 0.02434 0.01260 -0.1120 0.7700 0.0959
1.750 0.7221 0.02386 0.01204 -0.1117 0.7543 0.1012
2.000 0.7526 0.02341 0.01157 -0.1114 0.7377 0.1099
2.250 0.7837 0.02296 0.01119 -0.1113 0.7208 0.1338
2.500 0.8124 0.02136 0.01099 -0.1110 0.7020 1.0000
2.750 0.8408 0.02139 0.01071 -0.1103 0.6818 1.0000
3.000 0.8708 0.02139 0.01046 -0.1098 0.6624 1.0000
3.250 0.8983 0.02154 0.01041 -0.1091 0.6412 1.0000
3.500 0.9259 0.02172 0.01042 -0.1085 0.6201 1.0000
3.750 0.9529 0.02200 0.01051 -0.1078 0.5995 1.0000
4.000 0.9779 0.02238 0.01077 -0.1070 0.5781 1.0000
4.250 1.0035 0.02277 0.01107 -0.1062 0.5584 1.0000
4.500 1.0278 0.02324 0.01144 -0.1054 0.5390 1.0000
4.750 1.0512 0.02373 0.01187 -0.1044 0.5194 1.0000
5.000 1.0746 0.02422 0.01232 -0.1035 0.5006 1.0000
5.500 1.1196 0.02528 0.01327 -0.1014 0.4638 1.0000
5.750 1.1416 0.02586 0.01384 -0.1003 0.4466 1.0000
6.000 1.1637 0.02647 0.01450 -0.0993 0.4306 1.0000
6.250 1.1858 0.02711 0.01516 -0.0983 0.4157 1.0000
6.500 1.2079 0.02778 0.01589 -0.0974 0.4018 1.0000
6.750 1.2300 0.02849 0.01667 -0.0965 0.3886 1.0000
7.000 1.2522 0.02923 0.01752 -0.0956 0.3760 1.0000
7.250 1.2746 0.03000 0.01838 -0.0947 0.3641 1.0000
7.500 1.2951 0.03086 0.01942 -0.0937 0.3517 1.0000
7.750 1.3156 0.03176 0.02050 -0.0927 0.3398 1.0000
8.000 1.3366 0.03269 0.02164 -0.0917 0.3289 1.0000
8.250 1.3590 0.03359 0.02267 -0.0909 0.3191 1.0000
8.500 1.3775 0.03474 0.02414 -0.0897 0.3089 1.0000
8.750 1.3987 0.03585 0.02549 -0.0888 0.3006 1.0000
9.000 1.4165 0.03676 0.02661 -0.0874 0.2899 1.0000
9.250 1.4265 0.03757 0.02771 -0.0849 0.2760 1.0000
9.500 1.4334 0.03831 0.02868 -0.0821 0.2613 1.0000
9.750 1.4347 0.03898 0.02948 -0.0786 0.2446 1.0000
10.000 1.4299 0.03997 0.03071 -0.0746 0.2258 1.0000
10.250 1.4235 0.04118 0.03202 -0.0707 0.2058 1.0000
10.500 1.4163 0.04284 0.03371 -0.0674 0.1834 1.0000
10.750 1.4082 0.04507 0.03592 -0.0647 0.1590 1.0000
11.000 1.3998 0.04793 0.03879 -0.0626 0.1295 1.0000
11.500 1.3705 0.05621 0.04673 -0.0602 0.0655 1.0000
11.750 1.3539 0.06124 0.05170 -0.0601 0.0597 1.0000
12.000 1.3379 0.06661 0.05711 -0.0607 0.0558 1.0000
12.250 1.3242 0.07203 0.06272 -0.0616 0.0526 1.0000
12.500 1.3100 0.07783 0.06869 -0.0631 0.0502 1.0000
12.750 1.2961 0.08380 0.07483 -0.0649 0.0484 1.0000
13.000 1.2820 0.09000 0.08117 -0.0669 0.0468 1.0000
13.250 1.2686 0.09619 0.08746 -0.0690 0.0453 1.0000
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Polar data table (+)
Polar graphs
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