GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 50,000 Max Cl/Cd: 37.89 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe369-il-50000.txt Download as CSV file: xf-goe369-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3777 0.11063 0.10388 -0.0094 1.0000 0.0895
-8.250 -0.3807 0.10996 0.10334 -0.0119 1.0000 0.0904
-8.000 -0.3823 0.10954 0.10303 -0.0163 1.0000 0.0909
-7.750 -0.3602 0.10090 0.09438 -0.0112 1.0000 0.0960
-7.500 -0.3562 0.09837 0.09190 -0.0121 1.0000 0.0999
-7.250 -0.3535 0.09699 0.09062 -0.0160 1.0000 0.1032
-6.750 -0.3365 0.08962 0.08340 -0.0164 1.0000 0.1114
-6.500 -0.3286 0.08794 0.08177 -0.0209 1.0000 0.1167
-6.250 -0.3198 0.08427 0.07819 -0.0217 1.0000 0.1203
-6.000 -0.3100 0.08102 0.07500 -0.0215 1.0000 0.1277
-5.750 -0.2981 0.07889 0.07291 -0.0263 1.0000 0.1333
-5.500 -0.2898 0.07508 0.06919 -0.0240 1.0000 0.1412
-5.250 -0.2781 0.07238 0.06654 -0.0266 1.0000 0.1492
-5.000 -0.2626 0.07083 0.06496 -0.0305 1.0000 0.1617
-4.750 -0.2584 0.06673 0.06101 -0.0267 1.0000 0.1720
-4.500 -0.2504 0.06401 0.05837 -0.0264 1.0000 0.1838
-4.250 -0.2444 0.06168 0.05613 -0.0259 1.0000 0.1977
-4.000 -0.2419 0.05967 0.05418 -0.0247 1.0000 0.2132
-3.750 -0.2373 0.05848 0.05295 -0.0253 1.0000 0.2351
-3.500 -0.2393 0.05589 0.05050 -0.0219 1.0000 0.2530
-3.250 -0.2377 0.05386 0.04852 -0.0199 1.0000 0.2822
-3.000 -0.2364 0.05193 0.04665 -0.0176 1.0000 0.3245
-2.250 -0.2489 0.04465 0.03980 -0.0014 1.0000 0.4872
-2.000 -0.2486 0.04243 0.03767 0.0033 1.0000 0.5432
-1.750 -0.2489 0.03990 0.03528 0.0089 1.0000 0.5891
-1.500 -0.2434 0.03763 0.03309 0.0128 1.0000 0.6295
-1.250 -0.2262 0.03541 0.03087 0.0131 1.0000 0.6616
-1.000 -0.1885 0.03311 0.02851 0.0084 0.9971 0.6777
-0.750 0.0216 0.03385 0.02710 -0.0407 0.9827 0.3947
-0.500 0.1066 0.03361 0.02555 -0.0508 0.9710 0.2478
-0.250 0.1595 0.03244 0.02376 -0.0545 0.9595 0.1969
0.000 0.2100 0.03155 0.02226 -0.0576 0.9476 0.1657
0.250 0.2565 0.03076 0.02105 -0.0604 0.9354 0.1525
0.500 0.3059 0.03003 0.01991 -0.0636 0.9231 0.1518
0.750 0.3593 0.02938 0.01890 -0.0673 0.9111 0.1495
1.000 0.4083 0.02876 0.01815 -0.0705 0.8989 0.1621
1.250 0.4483 0.02840 0.01774 -0.0724 0.8855 0.1759
1.500 0.4891 0.02795 0.01757 -0.0748 0.8721 0.2247
1.750 0.5430 0.02652 0.01727 -0.0785 0.8590 1.0000
2.000 0.5814 0.02703 0.01737 -0.0799 0.8441 1.0000
2.250 0.6184 0.02751 0.01765 -0.0812 0.8286 1.0000
2.500 0.6538 0.02799 0.01800 -0.0820 0.8128 1.0000
2.750 0.6892 0.02839 0.01834 -0.0824 0.7966 1.0000
3.000 0.7147 0.02900 0.01891 -0.0814 0.7771 1.0000
3.250 0.7467 0.02906 0.01895 -0.0803 0.7554 1.0000
3.500 0.7754 0.02908 0.01898 -0.0784 0.7327 1.0000
3.750 0.8033 0.02904 0.01891 -0.0762 0.7105 1.0000
4.000 0.8280 0.02926 0.01915 -0.0741 0.6894 1.0000
4.250 0.8518 0.02946 0.01937 -0.0719 0.6674 1.0000
4.500 0.8766 0.02950 0.01943 -0.0695 0.6454 1.0000
4.750 0.9010 0.02940 0.01940 -0.0669 0.6216 1.0000
5.000 0.9237 0.02931 0.01934 -0.0642 0.5948 1.0000
5.250 0.9476 0.02888 0.01891 -0.0612 0.5659 1.0000
5.500 0.9723 0.02820 0.01817 -0.0581 0.5342 1.0000
5.750 0.9953 0.02768 0.01764 -0.0552 0.4985 1.0000
6.000 1.0186 0.02729 0.01708 -0.0524 0.4606 1.0000
6.250 1.0395 0.02753 0.01717 -0.0500 0.4212 1.0000
6.500 1.0616 0.02802 0.01736 -0.0479 0.3862 1.0000
6.750 1.0826 0.02917 0.01844 -0.0463 0.3557 1.0000
7.000 1.1052 0.03049 0.01958 -0.0451 0.3304 1.0000
7.250 1.1246 0.03211 0.02131 -0.0438 0.3076 1.0000
7.500 1.1466 0.03372 0.02291 -0.0427 0.2894 1.0000
7.750 1.1679 0.03558 0.02486 -0.0418 0.2744 1.0000
8.000 1.1877 0.03741 0.02688 -0.0407 0.2601 1.0000
8.250 1.2054 0.03960 0.02934 -0.0396 0.2482 1.0000
8.500 1.2224 0.04211 0.03213 -0.0386 0.2387 1.0000
8.750 1.2426 0.04417 0.03425 -0.0377 0.2283 1.0000
9.000 1.2533 0.04696 0.03748 -0.0363 0.2194 1.0000
9.250 1.2664 0.05020 0.04104 -0.0352 0.2135 1.0000
9.500 1.2642 0.05459 0.04600 -0.0337 0.2094 1.0000
9.750 1.2882 0.05684 0.04822 -0.0330 0.2013 1.0000
10.000 1.2704 0.06223 0.05420 -0.0313 0.1992 1.0000
10.250 1.2457 0.06818 0.06053 -0.0302 0.1982 1.0000
10.500 1.2130 0.07486 0.06742 -0.0299 0.1991 1.0000
10.750 1.1776 0.08185 0.07446 -0.0303 0.2006 1.0000
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Polar data table (+)
Polar graphs
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