GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 200,000 Max Cl/Cd: 82.6 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe155-il-200000.txt Download as CSV file: xf-goe155-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3115 0.09640 0.09323 -0.0277 1.0000 0.0298
-7.500 -0.3199 0.09556 0.09247 -0.0282 1.0000 0.0299
-7.250 -0.3292 0.09475 0.09173 -0.0281 0.9984 0.0300
-7.000 -0.2919 0.08979 0.08671 -0.0411 0.9918 0.0302
-6.750 -0.2807 0.08351 0.08045 -0.0401 0.9886 0.0308
-6.500 -0.2596 0.07915 0.07608 -0.0417 0.9854 0.0317
-6.250 -0.2304 0.07490 0.07180 -0.0478 0.9812 0.0331
-6.000 -0.1983 0.07059 0.06743 -0.0553 0.9751 0.0350
-5.750 -0.1265 0.06600 0.06254 -0.0776 0.9676 0.0389
-5.500 -0.1174 0.06060 0.05722 -0.0767 0.9615 0.0401
-5.250 -0.0934 0.05734 0.05395 -0.0787 0.9568 0.0418
-5.000 -0.0675 0.05432 0.05085 -0.0821 0.9477 0.0445
-4.750 -0.0129 0.04989 0.04601 -0.0939 0.9396 0.0498
-4.500 -0.0030 0.04691 0.04311 -0.0922 0.9309 0.0514
-4.250 0.0157 0.04494 0.04111 -0.0920 0.9215 0.0551
-4.000 0.0569 0.04156 0.03727 -0.0971 0.9136 0.0618
-3.750 0.0716 0.03908 0.03485 -0.0961 0.9032 0.0636
-3.500 0.0930 0.03715 0.03284 -0.0959 0.8950 0.0673
-3.250 0.1271 0.03446 0.02973 -0.0981 0.8875 0.0750
-3.000 0.1470 0.03261 0.02791 -0.0977 0.8809 0.0787
-2.750 0.1776 0.03057 0.02552 -0.0988 0.8738 0.0886
-2.500 0.2002 0.02888 0.02380 -0.0984 0.8680 0.0928
-2.250 0.2290 0.02717 0.02185 -0.0990 0.8604 0.1034
-2.000 0.2561 0.02594 0.02035 -0.0988 0.8550 0.1158
-1.750 0.2817 0.02459 0.01899 -0.0988 0.8471 0.1234
-1.500 0.3086 0.02361 0.01777 -0.0986 0.8411 0.1444
-1.250 0.3193 0.00712 0.00158 -0.0930 0.8174 0.1601
-1.000 0.3753 0.01816 0.01118 -0.0977 0.8280 0.0768
-0.750 0.4039 0.01680 0.00951 -0.0970 0.8206 0.0673
-0.500 0.4316 0.01576 0.00812 -0.0961 0.8126 0.0634
-0.250 0.4585 0.01508 0.00733 -0.0955 0.8031 0.0635
0.000 0.4846 0.01451 0.00669 -0.0946 0.7946 0.0659
0.250 0.5114 0.01395 0.00607 -0.0939 0.7839 0.0656
0.500 0.5379 0.01347 0.00556 -0.0932 0.7728 0.0659
0.750 0.5644 0.01307 0.00513 -0.0925 0.7623 0.0670
1.000 0.5912 0.01276 0.00478 -0.0919 0.7522 0.0694
1.250 0.6185 0.01255 0.00457 -0.0916 0.7413 0.0731
1.500 0.6458 0.01229 0.00431 -0.0912 0.7308 0.0831
1.750 0.6662 0.01055 0.00429 -0.0898 0.7215 0.7715
2.000 0.7006 0.01030 0.00412 -0.0906 0.7085 1.0000
2.250 0.7275 0.01036 0.00408 -0.0902 0.6950 1.0000
2.500 0.7543 0.01042 0.00404 -0.0898 0.6805 1.0000
2.750 0.7811 0.01048 0.00401 -0.0894 0.6651 1.0000
3.000 0.8078 0.01056 0.00400 -0.0889 0.6487 1.0000
3.250 0.8345 0.01065 0.00406 -0.0886 0.6294 1.0000
3.500 0.8611 0.01076 0.00410 -0.0882 0.6090 1.0000
3.750 0.8873 0.01092 0.00416 -0.0878 0.5873 1.0000
4.000 0.9134 0.01112 0.00426 -0.0874 0.5639 1.0000
4.250 0.9392 0.01137 0.00444 -0.0870 0.5403 1.0000
4.500 0.9646 0.01170 0.00463 -0.0865 0.5173 1.0000
4.750 0.9899 0.01205 0.00488 -0.0861 0.4931 1.0000
5.000 1.0146 0.01246 0.00517 -0.0856 0.4678 1.0000
5.250 1.0389 0.01292 0.00552 -0.0851 0.4438 1.0000
5.500 1.0635 0.01334 0.00589 -0.0847 0.4205 1.0000
5.750 1.0875 0.01380 0.00627 -0.0842 0.3968 1.0000
6.000 1.1115 0.01422 0.00665 -0.0837 0.3733 1.0000
6.250 1.1354 0.01463 0.00706 -0.0832 0.3509 1.0000
6.500 1.1589 0.01506 0.00746 -0.0826 0.3277 1.0000
6.750 1.1812 0.01556 0.00786 -0.0820 0.2951 1.0000
7.000 1.2014 0.01630 0.00842 -0.0811 0.2512 1.0000
7.250 1.2063 0.01891 0.00991 -0.0786 0.0812 1.0000
7.500 1.2201 0.02062 0.01149 -0.0767 0.0519 1.0000
7.750 1.2356 0.02197 0.01293 -0.0750 0.0450 1.0000
8.000 1.2511 0.02313 0.01425 -0.0733 0.0412 1.0000
8.250 1.2638 0.02443 0.01565 -0.0714 0.0380 1.0000
8.500 1.2715 0.02606 0.01735 -0.0689 0.0360 1.0000
8.750 1.2738 0.02810 0.01948 -0.0657 0.0345 1.0000
9.000 1.2779 0.03012 0.02155 -0.0625 0.0336 1.0000
9.250 1.2900 0.03145 0.02299 -0.0605 0.0326 1.0000
9.500 1.3024 0.03287 0.02450 -0.0586 0.0310 1.0000
9.750 1.3164 0.03454 0.02625 -0.0569 0.0297 1.0000
10.000 1.3345 0.03641 0.02820 -0.0555 0.0289 1.0000
10.250 1.3574 0.03854 0.03044 -0.0547 0.0282 1.0000
10.500 1.3846 0.04118 0.03328 -0.0545 0.0280 1.0000
10.750 1.4072 0.04384 0.03609 -0.0540 0.0274 1.0000
11.000 1.4242 0.04677 0.03913 -0.0534 0.0262 1.0000
11.250 1.4390 0.05006 0.04267 -0.0521 0.0260 1.0000
11.500 1.4367 0.05319 0.04639 -0.0481 0.0279 1.0000
11.750 1.4361 0.05890 0.05260 -0.0452 0.0313 1.0000
12.000 1.3125 0.05135 0.04531 -0.0302 0.0287 1.0000
12.250 1.2999 0.05640 0.05070 -0.0276 0.0303 1.0000
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Polar data table (+)
Polar graphs
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