GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 200,000 Max Cl/Cd: 73.44 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe365-il-200000-n5.txt Download as CSV file: xf-goe365-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 365 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2560 0.12405 0.12045 -0.0399 1.0000 0.0228
-11.000 -0.2543 0.12159 0.11804 -0.0399 1.0000 0.0240
-10.750 -0.2565 0.11913 0.11563 -0.0403 1.0000 0.0251
-10.500 -0.2505 0.11540 0.11192 -0.0442 0.9976 0.0254
-10.250 -0.2390 0.11105 0.10758 -0.0490 0.9918 0.0255
-10.000 -0.2278 0.10667 0.10321 -0.0540 0.9857 0.0256
-9.500 -0.2072 0.09810 0.09466 -0.0621 0.9673 0.0256
-9.250 -0.1949 0.09382 0.09039 -0.0657 0.9584 0.0257
-9.000 -0.1744 0.09084 0.08739 -0.0653 0.9529 0.0263
-8.750 -0.1562 0.08772 0.08425 -0.0680 0.9446 0.0277
-8.500 -0.1389 0.08295 0.07946 -0.0771 0.9344 0.0307
-8.250 -0.1225 0.07714 0.07362 -0.0882 0.9208 0.0310
-8.000 -0.1064 0.07158 0.06798 -0.0973 0.9062 0.0311
-7.750 -0.0902 0.06639 0.06267 -0.1042 0.8925 0.0312
-7.500 -0.0769 0.06161 0.05775 -0.1089 0.8790 0.0312
-7.250 -0.0617 0.05953 0.05571 -0.1078 0.8712 0.0321
-7.000 -0.0482 0.05715 0.05327 -0.1087 0.8600 0.0330
-6.750 -0.0353 0.05464 0.05066 -0.1102 0.8493 0.0356
-6.500 -0.0263 0.04960 0.04509 -0.1144 0.8371 0.0382
-6.250 -0.0138 0.04644 0.04170 -0.1144 0.8287 0.0383
-6.000 0.0003 0.04386 0.03927 -0.1139 0.8225 0.0369
-5.750 0.0129 0.04078 0.03603 -0.1136 0.8149 0.0349
-5.500 0.0297 0.03778 0.03274 -0.1135 0.8088 0.0362
-5.250 0.0449 0.03494 0.02966 -0.1127 0.8016 0.0353
-5.000 0.0622 0.03180 0.02616 -0.1118 0.7957 0.0340
-4.750 0.0810 0.02946 0.02352 -0.1107 0.7895 0.0341
-4.500 0.1015 0.02768 0.02144 -0.1097 0.7830 0.0355
-4.250 0.1234 0.02571 0.01910 -0.1087 0.7776 0.0357
-4.000 0.1443 0.02399 0.01709 -0.1075 0.7707 0.0356
-3.750 0.1677 0.02252 0.01528 -0.1065 0.7649 0.0359
-3.500 0.1922 0.02143 0.01387 -0.1057 0.7597 0.0371
-3.250 0.2162 0.02042 0.01260 -0.1048 0.7539 0.0376
-3.000 0.2417 0.01945 0.01139 -0.1041 0.7489 0.0377
-2.750 0.2676 0.01864 0.01037 -0.1036 0.7442 0.0379
-2.500 0.2926 0.01798 0.00955 -0.1029 0.7385 0.0382
-2.250 0.3184 0.01711 0.00856 -0.1024 0.7335 0.0391
-2.000 0.3448 0.01649 0.00789 -0.1021 0.7288 0.0402
-1.750 0.3697 0.01598 0.00735 -0.1014 0.7229 0.0407
-1.500 0.3956 0.01551 0.00682 -0.1009 0.7174 0.0410
-1.250 0.4220 0.01510 0.00636 -0.1004 0.7125 0.0415
-1.000 0.4462 0.01474 0.00601 -0.0996 0.7061 0.0421
-0.750 0.4715 0.01442 0.00567 -0.0990 0.7003 0.0428
-0.500 0.4965 0.01416 0.00539 -0.0983 0.6945 0.0435
-0.250 0.5206 0.01395 0.00519 -0.0975 0.6875 0.0453
0.000 0.5464 0.01378 0.00495 -0.0970 0.6812 0.0467
0.250 0.5693 0.01359 0.00479 -0.0959 0.6720 0.0475
0.500 0.5933 0.01338 0.00452 -0.0950 0.6624 0.0490
0.750 0.6169 0.01324 0.00432 -0.0939 0.6500 0.0508
1.000 0.6397 0.01313 0.00416 -0.0927 0.6347 0.0532
1.250 0.6627 0.01305 0.00402 -0.0916 0.6190 0.0563
1.500 0.6858 0.01297 0.00394 -0.0905 0.6044 0.0672
2.000 0.7895 0.01111 0.00415 -0.1011 0.5709 1.0000
2.250 0.8101 0.01126 0.00416 -0.0995 0.5551 1.0000
2.500 0.8303 0.01143 0.00420 -0.0979 0.5390 1.0000
2.750 0.8501 0.01163 0.00427 -0.0963 0.5224 1.0000
3.000 0.8694 0.01185 0.00437 -0.0946 0.5054 1.0000
3.250 0.8886 0.01210 0.00449 -0.0929 0.4888 1.0000
3.500 0.9072 0.01237 0.00464 -0.0910 0.4711 1.0000
3.750 0.9254 0.01267 0.00482 -0.0892 0.4531 1.0000
4.000 0.9431 0.01299 0.00501 -0.0873 0.4351 1.0000
4.250 0.9612 0.01331 0.00523 -0.0854 0.4187 1.0000
4.500 0.9790 0.01363 0.00545 -0.0836 0.4026 1.0000
4.750 0.9969 0.01395 0.00571 -0.0818 0.3869 1.0000
5.000 1.0149 0.01428 0.00596 -0.0800 0.3724 1.0000
5.250 1.0325 0.01461 0.00624 -0.0782 0.3579 1.0000
5.500 1.0493 0.01497 0.00654 -0.0763 0.3429 1.0000
5.750 1.0653 0.01535 0.00685 -0.0742 0.3276 1.0000
6.000 1.0801 0.01575 0.00719 -0.0720 0.3127 1.0000
6.250 1.0937 0.01616 0.00754 -0.0695 0.2985 1.0000
6.500 1.1071 0.01660 0.00793 -0.0671 0.2854 1.0000
6.750 1.1204 0.01707 0.00835 -0.0647 0.2733 1.0000
7.000 1.1333 0.01759 0.00880 -0.0623 0.2619 1.0000
7.250 1.1477 0.01807 0.00926 -0.0603 0.2521 1.0000
7.500 1.1619 0.01859 0.00977 -0.0583 0.2440 1.0000
7.750 1.1763 0.01911 0.01030 -0.0564 0.2370 1.0000
8.000 1.1904 0.01967 0.01085 -0.0545 0.2311 1.0000
8.250 1.2055 0.02022 0.01142 -0.0528 0.2250 1.0000
8.500 1.2185 0.02086 0.01207 -0.0509 0.2198 1.0000
8.750 1.2338 0.02144 0.01269 -0.0493 0.2155 1.0000
9.000 1.2489 0.02203 0.01333 -0.0478 0.2116 1.0000
9.250 1.2629 0.02270 0.01403 -0.0462 0.2080 1.0000
9.500 1.2758 0.02345 0.01481 -0.0446 0.2047 1.0000
9.750 1.2911 0.02409 0.01554 -0.0433 0.2017 1.0000
10.000 1.3060 0.02477 0.01629 -0.0420 0.1981 1.0000
10.250 1.3195 0.02554 0.01712 -0.0406 0.1944 1.0000
10.500 1.3320 0.02639 0.01802 -0.0391 0.1914 1.0000
10.750 1.3447 0.02724 0.01894 -0.0378 0.1864 1.0000
11.000 1.3573 0.02810 0.01988 -0.0365 0.1808 1.0000
11.250 1.3664 0.02920 0.02099 -0.0350 0.1755 1.0000
11.500 1.3789 0.03013 0.02202 -0.0339 0.1702 1.0000
11.750 1.3892 0.03121 0.02318 -0.0327 0.1638 1.0000
12.000 1.3974 0.03248 0.02448 -0.0314 0.1587 1.0000
12.250 1.4092 0.03352 0.02565 -0.0304 0.1516 1.0000
12.500 1.4158 0.03498 0.02713 -0.0292 0.1450 1.0000
12.750 1.4267 0.03615 0.02842 -0.0284 0.1370 1.0000
13.000 1.4339 0.03764 0.02998 -0.0274 0.1269 1.0000
13.250 1.4375 0.03948 0.03181 -0.0263 0.1118 1.0000
13.500 1.4351 0.04192 0.03416 -0.0252 0.0972 1.0000
13.750 1.4300 0.04471 0.03689 -0.0241 0.0877 1.0000
14.000 1.4301 0.04710 0.03935 -0.0233 0.0816 1.0000
14.250 1.4254 0.05008 0.04236 -0.0225 0.0740 1.0000
14.500 1.4256 0.05264 0.04501 -0.0220 0.0545 1.0000
14.750 1.4033 0.05783 0.05003 -0.0217 0.0336 1.0000
15.000 1.3881 0.06253 0.05477 -0.0217 0.0283 1.0000
15.250 1.3798 0.06661 0.05897 -0.0220 0.0258 1.0000
15.500 1.3697 0.07106 0.06356 -0.0226 0.0239 1.0000
16.000 1.3504 0.08040 0.07319 -0.0245 0.0216 1.0000
16.250 1.3415 0.08517 0.07812 -0.0258 0.0208 1.0000
16.500 1.3302 0.09043 0.08354 -0.0274 0.0201 1.0000
16.750 1.3173 0.09607 0.08934 -0.0292 0.0195 1.0000
17.000 1.3037 0.10199 0.09541 -0.0314 0.0190 1.0000
17.250 1.2884 0.10832 0.10189 -0.0338 0.0186 1.0000
17.500 1.2733 0.11477 0.10850 -0.0364 0.0184 1.0000
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