GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 50,000 Max Cl/Cd: 43.51 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe240-il-50000-n5.txt Download as CSV file: xf-goe240-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3080 0.10088 0.09443 -0.0263 1.0000 0.0839
-7.250 -0.3106 0.09899 0.09265 -0.0262 1.0000 0.0860
-7.000 -0.3142 0.09766 0.09144 -0.0275 1.0000 0.0883
-6.750 -0.3176 0.09695 0.09085 -0.0306 1.0000 0.0895
-6.500 -0.3173 0.09614 0.09009 -0.0346 1.0000 0.0901
-6.250 -0.3150 0.09021 0.08428 -0.0268 1.0000 0.0930
-6.000 -0.3147 0.08779 0.08193 -0.0253 1.0000 0.0960
-5.750 -0.3148 0.08575 0.07994 -0.0252 1.0000 0.0990
-5.500 -0.3117 0.08409 0.07830 -0.0279 1.0000 0.1026
-5.250 -0.2977 0.08294 0.07703 -0.0354 1.0000 0.1042
-5.000 -0.2982 0.07875 0.07297 -0.0314 1.0000 0.1055
-4.750 -0.2800 0.07469 0.06890 -0.0323 0.9958 0.1089
-4.500 -0.2339 0.07046 0.06445 -0.0438 0.9873 0.1195
-4.250 -0.1946 0.06673 0.06051 -0.0513 0.9793 0.1331
-4.000 -0.1710 0.06248 0.05628 -0.0523 0.9728 0.1389
-3.750 -0.1326 0.05877 0.05239 -0.0587 0.9655 0.1515
-3.500 -0.1015 0.05566 0.04917 -0.0623 0.9580 0.1691
-3.250 -0.0215 0.04905 0.04150 -0.0764 0.9524 0.0897
-3.000 0.0078 0.04561 0.03799 -0.0786 0.9456 0.0838
-2.750 0.0580 0.04181 0.03341 -0.0842 0.9393 0.0754
-2.500 0.0934 0.03929 0.03072 -0.0872 0.9331 0.0784
-2.250 0.1289 0.03716 0.02827 -0.0897 0.9254 0.0796
-2.000 0.1756 0.03467 0.02505 -0.0934 0.9206 0.0769
-1.750 0.2085 0.03314 0.02303 -0.0945 0.9114 0.0761
-1.500 0.2504 0.03141 0.02090 -0.0974 0.9062 0.0761
-1.250 0.2815 0.03014 0.01937 -0.0982 0.8969 0.0767
-1.000 0.3201 0.02897 0.01803 -0.1004 0.8906 0.0800
-0.750 0.3532 0.02818 0.01702 -0.1014 0.8817 0.0850
-0.500 0.3881 0.02735 0.01587 -0.1023 0.8736 0.0878
-0.250 0.4259 0.02655 0.01475 -0.1035 0.8662 0.0903
0.000 0.4582 0.02586 0.01399 -0.1040 0.8568 0.0942
0.250 0.4951 0.02515 0.01314 -0.1051 0.8491 0.1008
0.500 0.5281 0.02454 0.01248 -0.1055 0.8384 0.1109
0.750 0.5604 0.02391 0.01194 -0.1059 0.8265 0.1379
1.000 0.5904 0.02146 0.01159 -0.1059 0.8150 1.0000
1.250 0.6222 0.02147 0.01117 -0.1057 0.8026 1.0000
1.500 0.6539 0.02148 0.01091 -0.1057 0.7909 1.0000
1.750 0.6825 0.02161 0.01086 -0.1053 0.7780 1.0000
2.000 0.7091 0.02182 0.01095 -0.1046 0.7643 1.0000
2.250 0.7354 0.02203 0.01106 -0.1040 0.7505 1.0000
2.500 0.7615 0.02225 0.01120 -0.1033 0.7366 1.0000
2.750 0.7872 0.02246 0.01138 -0.1025 0.7224 1.0000
3.000 0.8127 0.02268 0.01156 -0.1017 0.7080 1.0000
3.250 0.8379 0.02289 0.01175 -0.1008 0.6932 1.0000
3.500 0.8629 0.02309 0.01198 -0.0999 0.6780 1.0000
3.750 0.8877 0.02328 0.01218 -0.0990 0.6623 1.0000
4.000 0.9125 0.02343 0.01233 -0.0979 0.6457 1.0000
4.250 0.9376 0.02343 0.01234 -0.0967 0.6269 1.0000
4.500 0.9597 0.02354 0.01246 -0.0951 0.6036 1.0000
4.750 0.9839 0.02353 0.01239 -0.0936 0.5806 1.0000
5.000 1.0073 0.02367 0.01248 -0.0922 0.5570 1.0000
5.250 1.0312 0.02393 0.01271 -0.0910 0.5356 1.0000
5.500 1.0541 0.02433 0.01311 -0.0898 0.5143 1.0000
5.750 1.0773 0.02476 0.01352 -0.0887 0.4938 1.0000
6.000 1.0987 0.02531 0.01414 -0.0875 0.4721 1.0000
6.250 1.1201 0.02588 0.01480 -0.0863 0.4511 1.0000
6.500 1.1410 0.02647 0.01544 -0.0851 0.4304 1.0000
6.750 1.1608 0.02713 0.01619 -0.0838 0.4089 1.0000
7.000 1.1805 0.02778 0.01684 -0.0823 0.3885 1.0000
7.250 1.1993 0.02853 0.01770 -0.0809 0.3680 1.0000
7.500 1.2180 0.02934 0.01856 -0.0795 0.3491 1.0000
7.750 1.2366 0.03021 0.01948 -0.0781 0.3319 1.0000
8.000 1.2554 0.03114 0.02049 -0.0768 0.3162 1.0000
8.250 1.2742 0.03212 0.02161 -0.0756 0.3020 1.0000
8.500 1.2925 0.03314 0.02284 -0.0743 0.2885 1.0000
8.750 1.3054 0.03412 0.02392 -0.0724 0.2712 1.0000
9.000 1.3135 0.03513 0.02500 -0.0700 0.2515 1.0000
9.250 1.3206 0.03626 0.02628 -0.0676 0.2323 1.0000
9.500 1.3279 0.03745 0.02762 -0.0653 0.2160 1.0000
9.750 1.3335 0.03873 0.02905 -0.0628 0.2016 1.0000
10.000 1.3340 0.04031 0.03069 -0.0602 0.1836 1.0000
10.250 1.3323 0.04228 0.03275 -0.0578 0.1619 1.0000
10.500 1.3297 0.04461 0.03514 -0.0559 0.1399 1.0000
10.750 1.3261 0.04737 0.03798 -0.0544 0.1081 1.0000
11.000 1.3187 0.05081 0.04130 -0.0532 0.0731 1.0000
11.250 1.3054 0.05510 0.04534 -0.0524 0.0644 1.0000
11.500 1.2936 0.05952 0.04977 -0.0519 0.0584 1.0000
11.750 1.2818 0.06416 0.05451 -0.0519 0.0542 1.0000
12.000 1.2682 0.06920 0.05961 -0.0523 0.0513 1.0000
12.250 1.2586 0.07393 0.06451 -0.0527 0.0483 1.0000
12.500 1.2502 0.07863 0.06943 -0.0533 0.0455 1.0000
12.750 1.2414 0.08349 0.07446 -0.0542 0.0435 1.0000
13.000 1.2327 0.08839 0.07949 -0.0551 0.0420 1.0000
13.250 1.2243 0.09325 0.08445 -0.0561 0.0407 1.0000
13.500 1.2196 0.09768 0.08904 -0.0568 0.0394 1.0000
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Polar data table (+)
Polar graphs
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