GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 50,000 Max Cl/Cd: 40.83 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe408-il-50000-n5.txt Download as CSV file: xf-goe408-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3764 0.10243 0.09573 -0.0242 1.0000 0.0835
-7.500 -0.3868 0.10100 0.09443 -0.0253 1.0000 0.0847
-7.250 -0.3921 0.09918 0.09269 -0.0281 1.0000 0.0853
-7.000 -0.3846 0.09413 0.08771 -0.0254 1.0000 0.0869
-6.750 -0.3788 0.09062 0.08425 -0.0235 1.0000 0.0898
-6.500 -0.3769 0.08776 0.08145 -0.0234 1.0000 0.0929
-6.250 -0.3764 0.08536 0.07909 -0.0252 1.0000 0.0969
-6.000 -0.3751 0.08384 0.07749 -0.0297 1.0000 0.0989
-5.750 -0.3706 0.07905 0.07286 -0.0261 1.0000 0.1011
-5.500 -0.3659 0.07613 0.06998 -0.0241 1.0000 0.1071
-5.250 -0.3599 0.07452 0.06820 -0.0282 1.0000 0.1137
-5.000 -0.3573 0.07035 0.06419 -0.0237 1.0000 0.1191
-4.500 -0.3440 0.06496 0.05867 -0.0240 1.0000 0.1303
-4.250 -0.3379 0.06210 0.05582 -0.0222 1.0000 0.1341
-3.750 -0.3236 0.05766 0.05115 -0.0210 1.0000 0.1596
-3.500 -0.2708 0.05084 0.04335 -0.0269 0.9934 0.0860
-3.250 -0.2396 0.04719 0.03944 -0.0292 0.9855 0.0834
-3.000 -0.2096 0.04451 0.03653 -0.0313 0.9764 0.0909
-2.750 -0.1763 0.04146 0.03292 -0.0330 0.9669 0.0887
-2.500 -0.1435 0.03894 0.02993 -0.0343 0.9573 0.0887
-2.250 -0.1131 0.03718 0.02780 -0.0353 0.9463 0.0947
-2.000 -0.0822 0.03525 0.02543 -0.0360 0.9353 0.0946
-1.750 -0.0499 0.03354 0.02326 -0.0367 0.9246 0.0942
-1.500 -0.0141 0.03199 0.02129 -0.0380 0.9151 0.0944
-1.250 0.0219 0.03088 0.01966 -0.0391 0.9048 0.0983
-1.000 0.0555 0.02963 0.01824 -0.0403 0.8940 0.1016
-0.750 0.0957 0.02847 0.01678 -0.0424 0.8853 0.1022
-0.500 0.1341 0.02748 0.01557 -0.0442 0.8754 0.1034
-0.250 0.1797 0.02661 0.01445 -0.0474 0.8659 0.1052
0.000 0.2313 0.02572 0.01335 -0.0516 0.8587 0.1094
0.250 0.2726 0.02509 0.01262 -0.0541 0.8478 0.1167
0.500 0.3165 0.02441 0.01186 -0.0570 0.8381 0.1223
0.750 0.3612 0.02382 0.01114 -0.0599 0.8284 0.1281
1.000 0.4005 0.02333 0.01068 -0.0621 0.8161 0.1368
1.250 0.4425 0.02288 0.01027 -0.0647 0.8040 0.1579
1.500 0.5614 0.02039 0.00964 -0.0839 0.7980 1.0000
1.750 0.5975 0.02042 0.00946 -0.0851 0.7831 1.0000
2.000 0.6325 0.02051 0.00940 -0.0862 0.7680 1.0000
2.250 0.6663 0.02064 0.00941 -0.0871 0.7527 1.0000
2.750 0.7286 0.02105 0.00967 -0.0879 0.7211 1.0000
3.000 0.7571 0.02132 0.00991 -0.0878 0.7050 1.0000
3.250 0.7846 0.02162 0.01019 -0.0876 0.6891 1.0000
3.500 0.8110 0.02195 0.01053 -0.0871 0.6731 1.0000
3.750 0.8365 0.02229 0.01089 -0.0864 0.6569 1.0000
4.000 0.8613 0.02264 0.01127 -0.0856 0.6408 1.0000
4.250 0.8852 0.02298 0.01168 -0.0846 0.6240 1.0000
4.500 0.9083 0.02327 0.01199 -0.0833 0.6054 1.0000
4.750 0.9319 0.02350 0.01221 -0.0820 0.5862 1.0000
5.000 0.9506 0.02383 0.01260 -0.0800 0.5657 1.0000
5.250 0.9710 0.02415 0.01300 -0.0782 0.5460 1.0000
5.500 0.9924 0.02449 0.01338 -0.0766 0.5278 1.0000
5.750 1.0129 0.02486 0.01382 -0.0750 0.5097 1.0000
6.000 1.0317 0.02530 0.01437 -0.0731 0.4906 1.0000
6.250 1.0512 0.02576 0.01496 -0.0713 0.4722 1.0000
6.500 1.0710 0.02623 0.01552 -0.0696 0.4541 1.0000
7.000 1.1078 0.02736 0.01688 -0.0658 0.4167 1.0000
7.250 1.1247 0.02800 0.01764 -0.0636 0.3967 1.0000
7.500 1.1411 0.02863 0.01839 -0.0614 0.3766 1.0000
7.750 1.1537 0.02936 0.01925 -0.0586 0.3540 1.0000
8.000 1.1661 0.03006 0.02000 -0.0558 0.3323 1.0000
8.250 1.1764 0.03087 0.02094 -0.0528 0.3099 1.0000
8.500 1.1854 0.03168 0.02179 -0.0497 0.2882 1.0000
8.750 1.1924 0.03263 0.02283 -0.0463 0.2654 1.0000
9.000 1.1977 0.03367 0.02394 -0.0428 0.2443 1.0000
9.250 1.1998 0.03480 0.02514 -0.0390 0.2227 1.0000
9.500 1.1982 0.03612 0.02644 -0.0348 0.2008 1.0000
9.750 1.1928 0.03773 0.02801 -0.0307 0.1748 1.0000
10.000 1.1859 0.03971 0.02991 -0.0269 0.1479 1.0000
10.250 1.1794 0.04201 0.03213 -0.0238 0.1238 1.0000
10.500 1.1724 0.04463 0.03474 -0.0211 0.1017 1.0000
10.750 1.1660 0.04746 0.03753 -0.0190 0.0869 1.0000
11.000 1.1594 0.05054 0.04058 -0.0174 0.0759 1.0000
11.250 1.1532 0.05379 0.04383 -0.0162 0.0684 1.0000
11.500 1.1455 0.05732 0.04732 -0.0153 0.0638 1.0000
11.750 1.1413 0.06074 0.05087 -0.0144 0.0589 1.0000
12.000 1.1378 0.06416 0.05440 -0.0136 0.0549 1.0000
12.250 1.1333 0.06771 0.05799 -0.0131 0.0517 1.0000
12.500 1.1317 0.07116 0.06157 -0.0123 0.0483 1.0000
12.750 1.1318 0.07454 0.06524 -0.0119 0.0459 1.0000
13.000 1.1306 0.07819 0.06912 -0.0116 0.0437 1.0000
13.250 1.1294 0.08189 0.07302 -0.0114 0.0422 1.0000
13.500 1.1268 0.08579 0.07715 -0.0115 0.0410 1.0000
13.750 1.1246 0.08964 0.08105 -0.0115 0.0392 1.0000
14.000 1.1164 0.09469 0.08629 -0.0126 0.0383 1.0000
14.250 1.1047 0.10037 0.09223 -0.0146 0.0379 1.0000
14.500 1.0905 0.10676 0.09887 -0.0173 0.0377 1.0000
14.750 1.0770 0.11332 0.10565 -0.0203 0.0378 1.0000
15.000 1.0604 0.12086 0.11338 -0.0241 0.0377 1.0000
15.250 1.0437 0.12898 0.12167 -0.0283 0.0379 1.0000
15.500 1.0296 0.13689 0.12969 -0.0325 0.0383 1.0000
15.750 1.0142 0.14571 0.13853 -0.0372 0.0386 1.0000
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Polar data table (+)
Polar graphs
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