GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 50,000 Max Cl/Cd: 32.74 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe55-il-50000-n5.txt Download as CSV file: xf-goe55-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 55 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6048 0.11140 0.10432 0.0327 1.0000 0.1158
-8.000 -0.6098 0.10889 0.10189 0.0276 1.0000 0.1187
-7.750 -0.6088 0.10563 0.09864 0.0177 1.0000 0.1196
-7.500 -0.5920 0.10037 0.09341 0.0256 1.0000 0.1230
-7.250 -0.5822 0.09682 0.08989 0.0242 1.0000 0.1286
-7.000 -0.5760 0.09307 0.08611 0.0109 1.0000 0.1341
-6.750 -0.5632 0.08875 0.08185 0.0163 1.0000 0.1372
-6.500 -0.5498 0.08496 0.07806 0.0146 1.0000 0.1410
-6.250 -0.5338 0.08062 0.07361 0.0044 1.0000 0.1492
-5.750 -0.4815 0.06650 0.05898 -0.0082 1.0000 0.0912
-5.500 -0.4604 0.06232 0.05470 -0.0106 1.0000 0.0899
-5.250 -0.4368 0.05795 0.05017 -0.0136 1.0000 0.0872
-5.000 -0.4007 0.05122 0.04272 -0.0209 1.0000 0.0797
-4.750 -0.3753 0.04770 0.03904 -0.0225 1.0000 0.0789
-4.500 -0.3473 0.04416 0.03523 -0.0245 1.0000 0.0782
-4.250 -0.3162 0.04069 0.03128 -0.0268 1.0000 0.0794
-4.000 -0.2858 0.03769 0.02784 -0.0285 1.0000 0.0805
-3.750 -0.2561 0.03505 0.02487 -0.0296 1.0000 0.0807
-3.500 -0.2263 0.03266 0.02216 -0.0304 1.0000 0.0809
-3.250 -0.1969 0.03059 0.01984 -0.0310 1.0000 0.0815
-3.000 -0.1676 0.02879 0.01783 -0.0314 1.0000 0.0826
-2.750 -0.1387 0.02736 0.01627 -0.0316 1.0000 0.0857
-2.500 -0.1091 0.02598 0.01464 -0.0318 1.0000 0.0894
-2.250 -0.0794 0.02465 0.01301 -0.0317 1.0000 0.0917
-2.000 -0.0508 0.02339 0.01165 -0.0315 1.0000 0.0937
-1.750 -0.0231 0.02229 0.01059 -0.0312 1.0000 0.0968
-1.500 0.0047 0.02141 0.00967 -0.0308 1.0000 0.1024
-1.250 0.0327 0.02057 0.00886 -0.0305 1.0000 0.1097
-1.000 0.0609 0.01980 0.00811 -0.0301 1.0000 0.1176
-0.750 0.0890 0.01903 0.00750 -0.0300 1.0000 0.1282
-0.500 0.1176 0.01836 0.00704 -0.0300 1.0000 0.1468
-0.250 0.1592 0.01766 0.00667 -0.0327 0.8651 0.1889
0.000 0.1832 0.01512 0.00619 -0.0300 0.6883 1.0000
0.250 0.2081 0.01577 0.00597 -0.0282 0.6100 1.0000
0.500 0.2346 0.01629 0.00592 -0.0274 0.5670 1.0000
0.750 0.2620 0.01676 0.00597 -0.0269 0.5390 1.0000
1.000 0.2898 0.01721 0.00609 -0.0265 0.5184 1.0000
1.250 0.3180 0.01763 0.00627 -0.0263 0.5020 1.0000
1.500 0.3464 0.01806 0.00652 -0.0261 0.4879 1.0000
1.750 0.3748 0.01849 0.00680 -0.0260 0.4750 1.0000
2.000 0.4032 0.01895 0.00713 -0.0258 0.4629 1.0000
2.250 0.4313 0.01942 0.00750 -0.0256 0.4498 1.0000
2.500 0.4594 0.01986 0.00787 -0.0254 0.4346 1.0000
2.750 0.4872 0.02031 0.00826 -0.0252 0.4189 1.0000
3.000 0.5148 0.02077 0.00870 -0.0249 0.4037 1.0000
3.250 0.5425 0.02125 0.00918 -0.0247 0.3893 1.0000
3.500 0.5700 0.02175 0.00971 -0.0245 0.3752 1.0000
3.750 0.5975 0.02228 0.01030 -0.0243 0.3615 1.0000
4.000 0.6250 0.02283 0.01091 -0.0240 0.3478 1.0000
4.250 0.6523 0.02342 0.01154 -0.0238 0.3343 1.0000
4.500 0.6794 0.02400 0.01221 -0.0235 0.3201 1.0000
4.750 0.7064 0.02453 0.01286 -0.0232 0.3028 1.0000
5.000 0.7332 0.02491 0.01339 -0.0229 0.2818 1.0000
5.250 0.7593 0.02500 0.01352 -0.0225 0.2594 1.0000
5.500 0.7857 0.02501 0.01370 -0.0222 0.2313 1.0000
5.750 0.8118 0.02508 0.01375 -0.0220 0.2008 1.0000
6.000 0.8375 0.02558 0.01414 -0.0218 0.1721 1.0000
6.250 0.8625 0.02663 0.01513 -0.0217 0.1454 1.0000
6.500 0.8868 0.02813 0.01661 -0.0215 0.1242 1.0000
6.750 0.9105 0.02981 0.01831 -0.0213 0.1100 1.0000
7.000 0.9336 0.03145 0.01999 -0.0209 0.1010 1.0000
7.250 0.9570 0.03322 0.02202 -0.0205 0.0940 1.0000
7.500 0.9793 0.03481 0.02367 -0.0202 0.0883 1.0000
7.750 1.0013 0.03674 0.02583 -0.0198 0.0839 1.0000
8.000 1.0225 0.03894 0.02835 -0.0194 0.0807 1.0000
8.250 1.0428 0.04121 0.03091 -0.0191 0.0783 1.0000
8.500 1.0621 0.04353 0.03342 -0.0187 0.0764 1.0000
8.750 1.0804 0.04596 0.03598 -0.0183 0.0749 1.0000
9.000 1.0934 0.04975 0.04031 -0.0184 0.0733 1.0000
9.250 1.1008 0.05423 0.04536 -0.0189 0.0715 1.0000
9.500 1.1023 0.05921 0.05082 -0.0199 0.0700 1.0000
9.750 1.0952 0.06511 0.05715 -0.0217 0.0691 1.0000
10.000 1.0699 0.07357 0.06599 -0.0264 0.0693 1.0000
10.250 1.0154 0.08955 0.08216 -0.0403 0.0713 1.0000
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Polar data table (+)
Polar graphs
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