GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 50,000 Max Cl/Cd: 41.01 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe379-il-50000-n5.txt Download as CSV file: xf-goe379-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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 -0.2865 0.10227 0.09605 -0.0276 1.0000 0.0603
-7.250 -0.2925 0.10127 0.09520 -0.0275 1.0000 0.0611
-7.000 -0.2953 0.10010 0.09416 -0.0283 1.0000 0.0616
-6.750 -0.2974 0.09896 0.09312 -0.0293 1.0000 0.0619
-6.500 -0.2982 0.09768 0.09192 -0.0302 1.0000 0.0621
-6.250 -0.2980 0.09641 0.09072 -0.0314 1.0000 0.0623
-6.000 -0.2984 0.09071 0.08515 -0.0261 1.0000 0.0636
-5.750 -0.2992 0.08768 0.08219 -0.0234 1.0000 0.0658
-5.500 -0.3000 0.08555 0.08012 -0.0223 1.0000 0.0678
-5.250 -0.2996 0.08357 0.07820 -0.0220 1.0000 0.0704
-5.000 -0.2959 0.08182 0.07646 -0.0232 1.0000 0.0732
-4.500 -0.2362 0.07359 0.06810 -0.0356 0.9843 0.0782
-4.250 -0.2062 0.06946 0.06386 -0.0402 0.9758 0.0821
-4.000 -0.1525 0.06700 0.06101 -0.0519 0.9655 0.0892
-3.750 -0.1271 0.06208 0.05609 -0.0545 0.9568 0.0907
-3.500 -0.0998 0.05815 0.05209 -0.0571 0.9478 0.0933
-3.000 -0.0042 0.04965 0.04265 -0.0686 0.9308 0.0491
-2.500 0.0683 0.04264 0.03502 -0.0746 0.9144 0.0489
-2.250 0.0998 0.03959 0.03169 -0.0762 0.9046 0.0481
-2.000 0.1408 0.03642 0.02803 -0.0788 0.8978 0.0481
-1.750 0.1728 0.03427 0.02561 -0.0801 0.8878 0.0537
-1.500 0.2081 0.03207 0.02288 -0.0811 0.8783 0.0583
-1.250 0.2502 0.02954 0.01954 -0.0826 0.8714 0.0619
-1.000 0.2823 0.02817 0.01786 -0.0833 0.8601 0.0774
-0.750 0.3168 0.02660 0.01576 -0.0837 0.8495 0.0889
-0.500 0.3582 0.02536 0.01418 -0.0857 0.8398 0.1119
-0.250 0.3999 0.02429 0.01268 -0.0874 0.8300 0.1313
0.000 0.4328 0.02355 0.01174 -0.0878 0.8172 0.1460
0.250 0.4633 0.02296 0.01107 -0.0878 0.8040 0.1640
0.500 0.4930 0.02247 0.01048 -0.0877 0.7908 0.1900
0.750 0.5221 0.02182 0.01002 -0.0877 0.7776 0.2459
1.000 0.5750 0.02010 0.00941 -0.0923 0.7653 1.0000
1.250 0.6019 0.02021 0.00920 -0.0917 0.7514 1.0000
1.500 0.6283 0.02034 0.00909 -0.0910 0.7373 1.0000
1.750 0.6543 0.02049 0.00904 -0.0902 0.7233 1.0000
2.000 0.6799 0.02065 0.00905 -0.0895 0.7092 1.0000
2.250 0.7053 0.02083 0.00910 -0.0887 0.6952 1.0000
2.500 0.7305 0.02103 0.00919 -0.0879 0.6809 1.0000
2.750 0.7554 0.02124 0.00934 -0.0871 0.6668 1.0000
3.000 0.7802 0.02148 0.00951 -0.0863 0.6528 1.0000
3.250 0.8049 0.02173 0.00972 -0.0855 0.6389 1.0000
3.500 0.8294 0.02200 0.00996 -0.0846 0.6250 1.0000
3.750 0.8540 0.02230 0.01029 -0.0838 0.6114 1.0000
4.000 0.8785 0.02261 0.01060 -0.0830 0.5980 1.0000
4.250 0.9031 0.02294 0.01095 -0.0823 0.5848 1.0000
4.500 0.9278 0.02329 0.01139 -0.0815 0.5721 1.0000
4.750 0.9512 0.02373 0.01191 -0.0807 0.5588 1.0000
5.000 0.9744 0.02420 0.01248 -0.0798 0.5456 1.0000
5.250 0.9975 0.02470 0.01311 -0.0789 0.5328 1.0000
5.500 1.0203 0.02520 0.01379 -0.0780 0.5195 1.0000
5.750 1.0427 0.02568 0.01442 -0.0769 0.5056 1.0000
6.000 1.0646 0.02619 0.01509 -0.0758 0.4917 1.0000
6.250 1.0864 0.02674 0.01584 -0.0747 0.4783 1.0000
6.500 1.1083 0.02732 0.01666 -0.0736 0.4660 1.0000
6.750 1.1310 0.02792 0.01758 -0.0726 0.4546 1.0000
7.000 1.1474 0.02828 0.01817 -0.0704 0.4336 1.0000
7.250 1.1566 0.02820 0.01805 -0.0666 0.3975 1.0000
7.500 1.1636 0.02859 0.01848 -0.0630 0.3608 1.0000
7.750 1.1682 0.02927 0.01911 -0.0593 0.3170 1.0000
8.000 1.1693 0.03041 0.02009 -0.0555 0.2537 1.0000
8.250 1.1617 0.03262 0.02155 -0.0514 0.1526 1.0000
8.500 1.1429 0.03625 0.02422 -0.0471 0.0571 1.0000
8.750 1.1383 0.03892 0.02682 -0.0442 0.0445 1.0000
9.000 1.1350 0.04156 0.02954 -0.0417 0.0393 1.0000
9.250 1.1315 0.04429 0.03245 -0.0398 0.0360 1.0000
9.500 1.1254 0.04742 0.03573 -0.0383 0.0339 1.0000
9.750 1.1208 0.05057 0.03923 -0.0372 0.0317 1.0000
10.000 1.1157 0.05397 0.04285 -0.0366 0.0304 1.0000
10.250 1.1097 0.05764 0.04672 -0.0363 0.0293 1.0000
10.500 1.1042 0.06140 0.05068 -0.0362 0.0287 1.0000
10.750 1.0982 0.06534 0.05480 -0.0363 0.0280 1.0000
11.000 1.0936 0.06918 0.05878 -0.0363 0.0274 1.0000
11.250 1.0906 0.07278 0.06253 -0.0363 0.0269 1.0000
11.500 1.0885 0.07619 0.06603 -0.0358 0.0262 1.0000
11.750 1.0926 0.07876 0.06873 -0.0345 0.0254 1.0000
12.000 1.1007 0.08103 0.07127 -0.0331 0.0240 1.0000
12.250 1.1118 0.08301 0.07350 -0.0315 0.0231 1.0000
12.500 1.1254 0.08508 0.07587 -0.0295 0.0222 1.0000
12.750 1.1373 0.08779 0.07891 -0.0280 0.0219 1.0000
13.000 1.1406 0.09166 0.08308 -0.0277 0.0218 1.0000
13.250 1.1381 0.09623 0.08795 -0.0285 0.0218 1.0000
13.500 1.1317 0.10136 0.09335 -0.0300 0.0219 1.0000
13.750 1.1225 0.10705 0.09929 -0.0322 0.0220 1.0000
14.000 1.1119 0.11308 0.10555 -0.0350 0.0221 1.0000
14.250 1.1002 0.11964 0.11231 -0.0384 0.0223 1.0000
14.500 1.0886 0.12648 0.11933 -0.0422 0.0225 1.0000
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Polar data table (+)
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