GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 100,000 Max Cl/Cd: 43.66 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe645-il-100000.txt Download as CSV file: xf-goe645-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2639 0.10580 0.10113 -0.0371 1.0000 0.1611
-9.250 -0.3114 0.10551 0.10107 -0.0374 1.0000 0.1620
-8.500 -0.5307 0.05604 0.05132 -0.0659 0.9829 0.0937
-8.250 -0.5287 0.04667 0.04119 -0.0739 0.9704 0.0937
-8.000 -0.5106 0.04137 0.03533 -0.0775 0.9595 0.0948
-7.750 -0.4706 0.03973 0.03377 -0.0806 0.9522 0.0979
-7.500 -0.4412 0.03697 0.03064 -0.0832 0.9420 0.1015
-7.250 -0.4156 0.03387 0.02685 -0.0849 0.9314 0.1049
-7.000 -0.3756 0.03154 0.02434 -0.0880 0.9245 0.1091
-6.750 -0.3441 0.03026 0.02290 -0.0891 0.9138 0.1150
-6.500 -0.3001 0.02826 0.02069 -0.0923 0.9077 0.1228
-6.250 -0.2682 0.02702 0.01918 -0.0932 0.8971 0.1320
-6.000 -0.2225 0.02558 0.01772 -0.0963 0.8910 0.1481
-5.750 -0.1905 0.02494 0.01726 -0.0968 0.8800 0.1658
-5.500 -0.1466 0.02462 0.01691 -0.0991 0.8728 0.1911
-5.250 -0.1168 0.02461 0.01684 -0.0990 0.8604 0.2082
-5.000 -0.0730 0.02440 0.01655 -0.1011 0.8534 0.2251
-4.750 -0.0458 0.02451 0.01680 -0.1004 0.8398 0.2357
-4.500 -0.0156 0.02440 0.01663 -0.1003 0.8280 0.2483
-4.250 0.0195 0.02435 0.01652 -0.1009 0.8182 0.2640
-4.000 0.0439 0.02430 0.01628 -0.0999 0.8044 0.2775
-3.750 0.0720 0.02398 0.01603 -0.0993 0.7924 0.2864
-3.500 0.1027 0.02335 0.01517 -0.0993 0.7820 0.2983
-3.250 0.1264 0.02313 0.01489 -0.0982 0.7684 0.3099
-3.000 0.1529 0.02278 0.01447 -0.0975 0.7569 0.3217
-2.750 0.1814 0.02238 0.01391 -0.0972 0.7464 0.3359
-2.500 0.2049 0.02226 0.01365 -0.0961 0.7336 0.3500
-2.250 0.2327 0.02198 0.01336 -0.0956 0.7237 0.3626
-2.000 0.2578 0.02180 0.01314 -0.0948 0.7122 0.3754
-1.750 0.2825 0.02171 0.01295 -0.0939 0.7013 0.3887
-1.500 0.3109 0.02152 0.01265 -0.0935 0.6921 0.4021
-1.250 0.3339 0.02145 0.01263 -0.0925 0.6808 0.4130
-1.000 0.3639 0.02123 0.01226 -0.0924 0.6728 0.4258
-0.750 0.3860 0.02128 0.01232 -0.0913 0.6614 0.4383
-0.500 0.4149 0.02109 0.01209 -0.0910 0.6535 0.4539
-0.250 0.4373 0.02108 0.01215 -0.0898 0.6423 0.4694
0.000 0.4639 0.02095 0.01199 -0.0892 0.6331 0.4856
0.250 0.4899 0.02080 0.01183 -0.0885 0.6229 0.5012
0.500 0.5152 0.02073 0.01178 -0.0878 0.6131 0.5174
0.750 0.5433 0.02054 0.01158 -0.0874 0.6043 0.5370
1.000 0.5679 0.02053 0.01166 -0.0866 0.5949 0.5598
1.250 0.5970 0.02030 0.01151 -0.0865 0.5869 0.5936
1.750 0.6992 0.01933 0.01132 -0.0946 0.5679 1.0000
2.000 0.7201 0.01974 0.01163 -0.0934 0.5584 1.0000
2.250 0.7482 0.01992 0.01157 -0.0931 0.5510 1.0000
2.500 0.7688 0.02035 0.01195 -0.0918 0.5419 1.0000
2.750 0.7957 0.02056 0.01199 -0.0914 0.5343 1.0000
3.000 0.8171 0.02101 0.01240 -0.0902 0.5257 1.0000
3.250 0.8429 0.02124 0.01249 -0.0896 0.5175 1.0000
3.500 0.8648 0.02166 0.01287 -0.0884 0.5087 1.0000
3.750 0.8900 0.02190 0.01299 -0.0877 0.5002 1.0000
4.000 0.9118 0.02232 0.01337 -0.0866 0.4913 1.0000
4.250 0.9370 0.02255 0.01350 -0.0859 0.4827 1.0000
4.500 0.9582 0.02299 0.01391 -0.0847 0.4738 1.0000
4.750 0.9830 0.02324 0.01407 -0.0839 0.4654 1.0000
5.000 1.0044 0.02372 0.01453 -0.0828 0.4571 1.0000
5.250 1.0276 0.02405 0.01482 -0.0819 0.4490 1.0000
5.500 1.0514 0.02450 0.01521 -0.0811 0.4418 1.0000
5.750 1.0708 0.02498 0.01573 -0.0797 0.4336 1.0000
6.000 1.1016 0.02523 0.01578 -0.0800 0.4276 1.0000
6.250 1.1138 0.02597 0.01671 -0.0777 0.4193 1.0000
6.500 1.1398 0.02632 0.01698 -0.0773 0.4133 1.0000
6.750 1.1607 0.02698 0.01767 -0.0762 0.4074 1.0000
7.000 1.1773 0.02770 0.01850 -0.0746 0.4009 1.0000
7.250 1.2042 0.02809 0.01881 -0.0744 0.3960 1.0000
7.500 1.2234 0.02884 0.01963 -0.0732 0.3907 1.0000
7.750 1.2373 0.02964 0.02055 -0.0713 0.3845 1.0000
8.000 1.2636 0.02997 0.02083 -0.0710 0.3795 1.0000
8.250 1.2846 0.03064 0.02153 -0.0701 0.3746 1.0000
8.500 1.2935 0.03163 0.02271 -0.0676 0.3688 1.0000
8.750 1.3159 0.03213 0.02322 -0.0668 0.3642 1.0000
9.000 1.3506 0.03240 0.02335 -0.0678 0.3603 1.0000
9.250 1.3468 0.03384 0.02510 -0.0637 0.3549 1.0000
9.500 1.3620 0.03444 0.02578 -0.0620 0.3494 1.0000
9.750 1.3970 0.03444 0.02565 -0.0629 0.3448 1.0000
10.000 1.3974 0.03581 0.02725 -0.0595 0.3401 1.0000
10.250 1.4005 0.03695 0.02855 -0.0565 0.3349 1.0000
10.500 1.4300 0.03700 0.02855 -0.0566 0.3300 1.0000
10.750 1.4430 0.03784 0.02946 -0.0548 0.3251 1.0000
11.000 1.4282 0.03945 0.03129 -0.0496 0.3201 1.0000
11.250 1.4544 0.03947 0.03129 -0.0492 0.3145 1.0000
11.500 1.4694 0.04011 0.03195 -0.0477 0.3091 1.0000
11.750 1.4433 0.04228 0.03435 -0.0420 0.3041 1.0000
12.000 1.4827 0.04167 0.03364 -0.0428 0.2977 1.0000
12.250 1.4725 0.04345 0.03557 -0.0392 0.2922 1.0000
12.500 1.4491 0.04602 0.03833 -0.0352 0.2865 1.0000
12.750 1.5112 0.04433 0.03642 -0.0373 0.2789 1.0000
13.000 1.4501 0.04924 0.04168 -0.0315 0.2740 1.0000
13.250 1.4753 0.04929 0.04169 -0.0310 0.2672 1.0000
13.500 1.4743 0.05143 0.04389 -0.0294 0.2614 1.0000
13.750 1.3577 0.06368 0.05653 -0.0272 0.2557 1.0000
14.000 1.4793 0.05528 0.04786 -0.0271 0.2503 1.0000
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Polar data table (+)
Polar graphs
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