GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.14 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe380-il-1000000-n5.txt Download as CSV file: xf-goe380-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2913 0.11653 0.11492 -0.0238 1.0000 0.0031
-9.750 -0.2867 0.11390 0.11230 -0.0241 1.0000 0.0031
-9.500 -0.2832 0.11107 0.10949 -0.0246 1.0000 0.0031
-9.250 -0.2783 0.10829 0.10672 -0.0253 0.9999 0.0031
-8.250 -0.2290 0.09412 0.09258 -0.0363 0.9815 0.0033
-8.000 -0.2137 0.09074 0.08920 -0.0398 0.9760 0.0033
-7.750 -0.1948 0.08714 0.08560 -0.0444 0.9690 0.0034
-7.500 -0.1711 0.08319 0.08163 -0.0504 0.9623 0.0035
-7.250 -0.1395 0.07872 0.07713 -0.0589 0.9506 0.0037
-7.000 -0.1083 0.07441 0.07273 -0.0674 0.9275 0.0037
-6.750 -0.0893 0.07107 0.06926 -0.0719 0.8907 0.0038
-6.500 -0.0784 0.06847 0.06654 -0.0737 0.8632 0.0038
-6.250 -0.0689 0.06602 0.06394 -0.0750 0.8297 0.0039
-6.000 -0.0564 0.06339 0.06122 -0.0768 0.8106 0.0042
-5.750 -0.0423 0.06063 0.05838 -0.0788 0.7922 0.0043
-5.500 -0.0257 0.05776 0.05541 -0.0811 0.7748 0.0047
-5.250 -0.0066 0.05486 0.05241 -0.0835 0.7574 0.0049
-5.000 0.0152 0.05173 0.04917 -0.0862 0.7378 0.0050
-4.500 0.0582 0.04585 0.04300 -0.0902 0.6899 0.0051
-4.000 0.0999 0.04009 0.03690 -0.0929 0.6344 0.0042
-3.750 0.1252 0.03693 0.03354 -0.0944 0.6111 0.0039
-3.500 0.1510 0.03401 0.03043 -0.0954 0.5903 0.0041
-3.250 0.1775 0.03110 0.02733 -0.0961 0.5751 0.0042
-3.000 0.2046 0.02813 0.02416 -0.0965 0.5635 0.0047
-2.750 0.2311 0.02529 0.02110 -0.0964 0.5531 0.0047
-2.500 0.2574 0.02233 0.01790 -0.0960 0.5442 0.0045
-2.250 0.2833 0.01856 0.01377 -0.0950 0.5368 0.0042
-2.000 0.3060 0.01146 0.00575 -0.0924 0.5313 0.0040
-1.750 0.3316 0.01032 0.00428 -0.0916 0.5232 0.0042
-1.500 0.3577 0.00965 0.00341 -0.0910 0.5149 0.0046
-1.250 0.3839 0.00929 0.00290 -0.0906 0.5079 0.0051
-1.000 0.4098 0.00884 0.00233 -0.0900 0.5013 0.0055
-0.750 0.4361 0.00871 0.00216 -0.0897 0.4946 0.0065
-0.500 0.4626 0.00853 0.00193 -0.0893 0.4882 0.0075
-0.250 0.4889 0.00841 0.00173 -0.0889 0.4811 0.0083
0.000 0.5151 0.00822 0.00143 -0.0885 0.4735 0.0111
0.250 0.5414 0.00817 0.00132 -0.0881 0.4652 0.0146
0.500 0.5678 0.00812 0.00125 -0.0878 0.4543 0.0275
0.750 0.5940 0.00811 0.00126 -0.0874 0.4430 0.0532
1.000 0.6201 0.00817 0.00127 -0.0871 0.4276 0.0617
1.250 0.6462 0.00826 0.00131 -0.0868 0.4113 0.0735
1.500 0.6719 0.00838 0.00136 -0.0864 0.3929 0.0800
1.750 0.6977 0.00851 0.00140 -0.0860 0.3752 0.0843
2.000 0.7233 0.00864 0.00145 -0.0856 0.3591 0.0880
2.250 0.7489 0.00876 0.00153 -0.0853 0.3449 0.0928
2.500 0.7747 0.00889 0.00160 -0.0849 0.3335 0.0962
2.750 0.8006 0.00901 0.00167 -0.0846 0.3239 0.0981
3.000 0.8266 0.00909 0.00174 -0.0843 0.3173 0.1017
3.250 0.8527 0.00916 0.00182 -0.0841 0.3116 0.1059
3.500 0.8785 0.00927 0.00191 -0.0838 0.3059 0.1094
3.750 0.9047 0.00935 0.00200 -0.0835 0.3008 0.1133
4.000 0.9304 0.00945 0.00212 -0.0832 0.2944 0.1219
4.250 0.9515 0.00891 0.00239 -0.0822 0.2892 0.5955
4.500 1.0116 0.00830 0.00265 -0.0900 0.2816 1.0000
4.750 1.0359 0.00846 0.00278 -0.0894 0.2762 1.0000
5.000 1.0605 0.00859 0.00292 -0.0888 0.2699 1.0000
5.250 1.0844 0.00878 0.00308 -0.0882 0.2619 1.0000
5.500 1.1086 0.00893 0.00325 -0.0876 0.2539 1.0000
5.750 1.1313 0.00922 0.00345 -0.0867 0.2354 1.0000
6.000 1.1500 0.00984 0.00381 -0.0853 0.1899 1.0000
6.250 1.1693 0.01041 0.00421 -0.0839 0.1583 1.0000
6.500 1.1889 0.01096 0.00463 -0.0826 0.1311 1.0000
6.750 1.2037 0.01193 0.00527 -0.0806 0.0792 1.0000
7.000 1.2137 0.01333 0.00635 -0.0777 0.0098 1.0000
7.250 1.2348 0.01374 0.00677 -0.0766 0.0062 1.0000
7.500 1.2557 0.01415 0.00722 -0.0756 0.0046 1.0000
7.750 1.2762 0.01459 0.00768 -0.0744 0.0035 1.0000
8.000 1.2960 0.01507 0.00825 -0.0732 0.0030 1.0000
8.250 1.3156 0.01555 0.00879 -0.0719 0.0026 1.0000
8.500 1.3344 0.01607 0.00937 -0.0705 0.0024 1.0000
8.750 1.3514 0.01671 0.01007 -0.0689 0.0021 1.0000
9.000 1.3685 0.01729 0.01072 -0.0673 0.0018 1.0000
9.250 1.3850 0.01789 0.01139 -0.0656 0.0016 1.0000
9.500 1.4000 0.01854 0.01211 -0.0637 0.0014 1.0000
9.750 1.4102 0.01932 0.01299 -0.0609 0.0014 1.0000
10.000 1.4211 0.01997 0.01370 -0.0583 0.0012 1.0000
10.250 1.4280 0.02088 0.01475 -0.0552 0.0012 1.0000
10.500 1.4349 0.02181 0.01576 -0.0523 0.0011 1.0000
10.750 1.4335 0.02328 0.01737 -0.0484 0.0010 1.0000
11.000 1.4336 0.02476 0.01897 -0.0452 0.0010 1.0000
11.250 1.4379 0.02606 0.02038 -0.0427 0.0010 1.0000
11.500 1.4371 0.02782 0.02226 -0.0401 0.0010 1.0000
11.750 1.4382 0.02959 0.02416 -0.0380 0.0009 1.0000
12.000 1.4337 0.03200 0.02671 -0.0358 0.0008 1.0000
12.250 1.4315 0.03439 0.02922 -0.0344 0.0008 1.0000
12.500 1.4229 0.03763 0.03262 -0.0330 0.0008 1.0000
12.750 1.4156 0.04100 0.03613 -0.0321 0.0007 1.0000
13.000 1.4113 0.04422 0.03946 -0.0318 0.0008 1.0000
13.250 1.4051 0.04783 0.04320 -0.0317 0.0008 1.0000
13.500 1.3951 0.05204 0.04756 -0.0317 0.0008 1.0000
13.750 1.3853 0.05641 0.05208 -0.0320 0.0007 1.0000
14.000 1.3782 0.06050 0.05631 -0.0324 0.0007 1.0000
14.250 1.3709 0.06478 0.06071 -0.0330 0.0007 1.0000
14.500 1.3624 0.06930 0.06538 -0.0337 0.0007 1.0000
14.750 1.3549 0.07383 0.07004 -0.0348 0.0007 1.0000
15.000 1.3441 0.07894 0.07530 -0.0358 0.0007 1.0000
15.250 1.3381 0.08358 0.08006 -0.0373 0.0006 1.0000
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Polar data table (+)
Polar graphs
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