GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 200,000 Max Cl/Cd: 78.15 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe240-il-200000-n5.txt Download as CSV file: xf-goe240-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2980 0.09648 0.09313 -0.0274 1.0000 0.0219
-7.750 -0.3007 0.09447 0.09118 -0.0267 1.0000 0.0227
-7.500 -0.3094 0.09307 0.08986 -0.0252 1.0000 0.0234
-7.250 -0.2932 0.08937 0.08618 -0.0329 0.9937 0.0239
-7.000 -0.2632 0.08426 0.08103 -0.0440 0.9864 0.0241
-6.750 -0.2360 0.07920 0.07594 -0.0516 0.9795 0.0241
-6.500 -0.2077 0.07407 0.07076 -0.0588 0.9730 0.0241
-6.250 -0.1814 0.06916 0.06580 -0.0645 0.9655 0.0241
-6.000 -0.1509 0.06403 0.06060 -0.0720 0.9554 0.0242
-5.750 -0.1404 0.06232 0.05894 -0.0693 0.9497 0.0270
-5.500 -0.0917 0.05746 0.05387 -0.0821 0.9363 0.0318
-5.250 -0.0637 0.05308 0.04936 -0.0865 0.9226 0.0319
-5.000 -0.0370 0.04871 0.04486 -0.0900 0.9085 0.0319
-4.750 -0.0213 0.04578 0.04192 -0.0905 0.8948 0.0340
-4.250 0.0455 0.03731 0.03298 -0.0986 0.8727 0.0340
-4.000 0.0753 0.03461 0.03007 -0.1007 0.8636 0.0354
-3.750 0.1062 0.03171 0.02690 -0.1027 0.8542 0.0373
-3.500 0.1397 0.02731 0.02203 -0.1049 0.8459 0.0352
-3.250 0.1699 0.02459 0.01894 -0.1059 0.8381 0.0357
-3.000 0.1991 0.02258 0.01659 -0.1065 0.8306 0.0374
-2.750 0.2288 0.02017 0.01372 -0.1069 0.8235 0.0369
-2.500 0.2577 0.01827 0.01140 -0.1070 0.8161 0.0369
-2.250 0.2863 0.01688 0.00963 -0.1070 0.8092 0.0372
-2.000 0.3144 0.01598 0.00846 -0.1069 0.8022 0.0385
-1.750 0.3422 0.01522 0.00745 -0.1068 0.7944 0.0395
-1.500 0.3697 0.01448 0.00650 -0.1065 0.7852 0.0394
-1.250 0.3970 0.01390 0.00574 -0.1061 0.7759 0.0395
-1.000 0.4240 0.01340 0.00513 -0.1058 0.7651 0.0397
-0.750 0.4510 0.01299 0.00464 -0.1054 0.7544 0.0401
-0.500 0.4780 0.01266 0.00422 -0.1051 0.7449 0.0406
-0.250 0.5051 0.01238 0.00391 -0.1048 0.7354 0.0412
0.000 0.5323 0.01216 0.00366 -0.1046 0.7264 0.0419
0.250 0.5595 0.01197 0.00342 -0.1043 0.7171 0.0434
0.500 0.5866 0.01183 0.00331 -0.1041 0.7065 0.0467
0.750 0.6138 0.01175 0.00322 -0.1038 0.6960 0.0505
1.000 0.6408 0.01168 0.00316 -0.1035 0.6843 0.0545
1.250 0.6676 0.01164 0.00312 -0.1032 0.6698 0.0668
1.500 0.6942 0.01161 0.00308 -0.1028 0.6517 0.0866
1.750 0.7203 0.01161 0.00303 -0.1023 0.6288 0.1069
2.000 0.7451 0.01123 0.00310 -0.1019 0.6007 0.3276
2.250 0.7694 0.01012 0.00309 -0.1009 0.5738 1.0000
2.500 0.7947 0.01035 0.00315 -0.1003 0.5526 1.0000
2.750 0.8202 0.01060 0.00324 -0.0998 0.5331 1.0000
3.000 0.8454 0.01088 0.00337 -0.0992 0.5131 1.0000
3.250 0.8702 0.01118 0.00354 -0.0986 0.4912 1.0000
3.500 0.8951 0.01147 0.00371 -0.0981 0.4665 1.0000
3.750 0.9198 0.01177 0.00389 -0.0975 0.4390 1.0000
4.000 0.9440 0.01211 0.00410 -0.0969 0.4082 1.0000
4.250 0.9677 0.01250 0.00432 -0.0962 0.3771 1.0000
4.500 0.9911 0.01293 0.00459 -0.0955 0.3497 1.0000
4.750 1.0147 0.01335 0.00490 -0.0949 0.3281 1.0000
5.000 1.0387 0.01373 0.00523 -0.0943 0.3101 1.0000
5.250 1.0627 0.01411 0.00557 -0.0938 0.2934 1.0000
5.500 1.0866 0.01449 0.00592 -0.0932 0.2767 1.0000
5.750 1.1103 0.01488 0.00630 -0.0926 0.2593 1.0000
6.000 1.1336 0.01531 0.00669 -0.0919 0.2411 1.0000
6.250 1.1563 0.01578 0.00712 -0.0912 0.2212 1.0000
6.500 1.1768 0.01647 0.00762 -0.0903 0.1898 1.0000
6.750 1.1965 0.01723 0.00821 -0.0892 0.1639 1.0000
7.000 1.2177 0.01782 0.00878 -0.0883 0.1491 1.0000
7.250 1.2387 0.01841 0.00934 -0.0874 0.1350 1.0000
7.500 1.2596 0.01900 0.00992 -0.0865 0.1210 1.0000
7.750 1.2791 0.01971 0.01054 -0.0854 0.0954 1.0000
8.000 1.2923 0.02100 0.01157 -0.0836 0.0564 1.0000
8.250 1.3099 0.02185 0.01247 -0.0821 0.0457 1.0000
8.500 1.3244 0.02296 0.01351 -0.0803 0.0228 1.0000
8.750 1.3388 0.02405 0.01461 -0.0785 0.0177 1.0000
9.000 1.3534 0.02506 0.01574 -0.0766 0.0160 1.0000
9.250 1.3661 0.02614 0.01698 -0.0745 0.0147 1.0000
9.500 1.3750 0.02735 0.01840 -0.0719 0.0138 1.0000
9.750 1.3831 0.02860 0.01982 -0.0693 0.0131 1.0000
10.000 1.3915 0.02982 0.02121 -0.0670 0.0124 1.0000
10.250 1.3977 0.03124 0.02279 -0.0646 0.0117 1.0000
10.500 1.4017 0.03287 0.02458 -0.0622 0.0113 1.0000
10.750 1.4039 0.03473 0.02660 -0.0599 0.0109 1.0000
11.000 1.4045 0.03684 0.02885 -0.0578 0.0106 1.0000
11.250 1.4040 0.03918 0.03134 -0.0561 0.0103 1.0000
11.500 1.4026 0.04177 0.03407 -0.0546 0.0101 1.0000
11.750 1.4002 0.04458 0.03701 -0.0534 0.0099 1.0000
12.000 1.3968 0.04762 0.04020 -0.0523 0.0097 1.0000
12.250 1.3926 0.05083 0.04355 -0.0515 0.0095 1.0000
12.500 1.3875 0.05425 0.04708 -0.0507 0.0094 1.0000
12.750 1.3812 0.05788 0.05080 -0.0500 0.0092 1.0000
13.000 1.3743 0.06166 0.05466 -0.0491 0.0089 1.0000
13.250 1.3740 0.06482 0.05801 -0.0491 0.0087 1.0000
13.500 1.3724 0.06820 0.06157 -0.0493 0.0085 1.0000
13.750 1.3699 0.07183 0.06536 -0.0496 0.0083 1.0000
14.000 1.3665 0.07567 0.06937 -0.0501 0.0081 1.0000
14.250 1.3623 0.07971 0.07358 -0.0507 0.0079 1.0000
14.500 1.3573 0.08396 0.07799 -0.0514 0.0078 1.0000
14.750 1.3519 0.08841 0.08261 -0.0524 0.0077 1.0000
15.000 1.3458 0.09310 0.08746 -0.0536 0.0076 1.0000
15.250 1.3388 0.09802 0.09256 -0.0551 0.0076 1.0000
15.500 1.3311 0.10323 0.09794 -0.0569 0.0075 1.0000
15.750 1.3227 0.10872 0.10360 -0.0590 0.0074 1.0000
16.000 1.3137 0.11450 0.10959 -0.0615 0.0074 1.0000
16.250 1.3042 0.12057 0.11583 -0.0644 0.0074 1.0000
16.500 1.2941 0.12695 0.12238 -0.0677 0.0073 1.0000
16.750 1.2836 0.13365 0.12926 -0.0713 0.0073 1.0000
17.000 1.2728 0.14071 0.13649 -0.0754 0.0073 1.0000
17.250 1.2615 0.14818 0.14413 -0.0799 0.0074 1.0000
17.500 1.2499 0.15604 0.15215 -0.0848 0.0074 1.0000
17.750 1.2378 0.16439 0.16067 -0.0901 0.0074 1.0000
18.000 1.2253 0.17331 0.16971 -0.0959 0.0075 1.0000
18.250 1.2121 0.18304 0.17959 -0.1022 0.0076 1.0000
18.500 1.1979 0.19387 0.19054 -0.1092 0.0077 1.0000
18.750 1.1824 0.20626 0.20302 -0.1169 0.0079 1.0000
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