GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 50,000 Max Cl/Cd: 32.26 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe655-il-50000-n5.txt Download as CSV file: xf-goe655-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3443 0.09579 0.08909 -0.0451 1.0000 0.0781
-9.000 -0.3520 0.09301 0.08641 -0.0441 1.0000 0.0778
-8.750 -0.3633 0.09034 0.08385 -0.0429 1.0000 0.0774
-8.500 -0.3806 0.08767 0.08130 -0.0415 1.0000 0.0771
-8.250 -0.4015 0.08525 0.07901 -0.0397 1.0000 0.0768
-8.000 -0.4231 0.08224 0.07611 -0.0388 1.0000 0.0764
-7.750 -0.4440 0.07849 0.07242 -0.0388 1.0000 0.0762
-7.500 -0.4563 0.07279 0.06666 -0.0420 0.9965 0.0762
-7.250 -0.4508 0.06414 0.05764 -0.0512 0.9846 0.0768
-7.000 -0.4411 0.05719 0.05018 -0.0572 0.9738 0.0773
-6.750 -0.4258 0.05190 0.04433 -0.0608 0.9637 0.0777
-6.500 -0.4055 0.04751 0.03934 -0.0634 0.9547 0.0787
-6.250 -0.3777 0.04550 0.03725 -0.0652 0.9465 0.0810
-6.000 -0.3528 0.04340 0.03492 -0.0663 0.9375 0.0835
-5.750 -0.3232 0.04076 0.03181 -0.0682 0.9297 0.0858
-5.500 -0.2986 0.03853 0.02913 -0.0687 0.9202 0.0875
-5.250 -0.2649 0.03644 0.02644 -0.0705 0.9130 0.0906
-5.000 -0.2394 0.03518 0.02513 -0.0706 0.9031 0.0939
-4.750 -0.2030 0.03387 0.02365 -0.0724 0.8962 0.0981
-4.500 -0.1768 0.03273 0.02225 -0.0722 0.8857 0.1016
-4.250 -0.1375 0.03151 0.02086 -0.0741 0.8792 0.1074
-4.000 -0.1119 0.03077 0.02007 -0.0738 0.8677 0.1139
-3.750 -0.0761 0.02978 0.01897 -0.0749 0.8592 0.1222
-3.500 -0.0413 0.02892 0.01801 -0.0758 0.8491 0.1346
-3.250 -0.0098 0.02811 0.01723 -0.0762 0.8375 0.1513
-3.000 0.0301 0.02707 0.01631 -0.0780 0.8287 0.1845
-2.750 0.0599 0.02627 0.01571 -0.0781 0.8163 0.2336
-2.500 0.0875 0.02568 0.01532 -0.0777 0.8038 0.2944
-2.250 0.1182 0.02512 0.01492 -0.0778 0.7928 0.3588
-2.000 0.1494 0.02454 0.01455 -0.0777 0.7825 0.4318
-1.750 0.1729 0.02409 0.01434 -0.0763 0.7696 0.5013
-1.500 0.1996 0.02353 0.01402 -0.0752 0.7581 0.5709
-1.250 0.2314 0.02280 0.01360 -0.0744 0.7485 0.6617
-1.000 0.2719 0.02227 0.01344 -0.0751 0.7356 0.8112
-0.750 0.3688 0.02184 0.01274 -0.0873 0.7225 1.0000
-0.500 0.3943 0.02182 0.01241 -0.0867 0.7090 1.0000
-0.250 0.4222 0.02180 0.01208 -0.0864 0.6962 1.0000
0.000 0.4449 0.02191 0.01196 -0.0853 0.6814 1.0000
0.250 0.4670 0.02207 0.01191 -0.0841 0.6665 1.0000
0.500 0.4897 0.02224 0.01188 -0.0829 0.6517 1.0000
0.750 0.5129 0.02242 0.01186 -0.0819 0.6375 1.0000
1.000 0.5368 0.02260 0.01185 -0.0809 0.6236 1.0000
1.250 0.5618 0.02276 0.01181 -0.0801 0.6104 1.0000
1.500 0.5865 0.02296 0.01183 -0.0793 0.5974 1.0000
1.750 0.6085 0.02327 0.01200 -0.0781 0.5838 1.0000
2.000 0.6315 0.02358 0.01218 -0.0772 0.5714 1.0000
2.250 0.6567 0.02385 0.01229 -0.0765 0.5602 1.0000
2.500 0.6815 0.02415 0.01245 -0.0758 0.5492 1.0000
2.750 0.7034 0.02458 0.01279 -0.0748 0.5378 1.0000
3.000 0.7296 0.02491 0.01297 -0.0744 0.5286 1.0000
3.250 0.7520 0.02538 0.01339 -0.0735 0.5187 1.0000
3.500 0.7761 0.02583 0.01375 -0.0729 0.5100 1.0000
3.750 0.7998 0.02630 0.01415 -0.0722 0.5012 1.0000
4.000 0.8227 0.02682 0.01463 -0.0714 0.4930 1.0000
4.250 0.8459 0.02735 0.01511 -0.0707 0.4851 1.0000
4.500 0.8696 0.02789 0.01561 -0.0701 0.4779 1.0000
4.750 0.8903 0.02849 0.01621 -0.0690 0.4696 1.0000
5.000 0.9138 0.02897 0.01664 -0.0683 0.4618 1.0000
5.250 0.9331 0.02953 0.01720 -0.0670 0.4525 1.0000
5.500 0.9528 0.03005 0.01769 -0.0658 0.4432 1.0000
5.750 0.9752 0.03042 0.01800 -0.0648 0.4339 1.0000
6.000 0.9905 0.03110 0.01874 -0.0630 0.4245 1.0000
6.250 1.0152 0.03147 0.01903 -0.0624 0.4168 1.0000
6.500 1.0289 0.03235 0.02001 -0.0606 0.4089 1.0000
6.750 1.0513 0.03285 0.02050 -0.0598 0.4017 1.0000
7.000 1.0666 0.03370 0.02144 -0.0582 0.3944 1.0000
7.250 1.0848 0.03439 0.02217 -0.0569 0.3871 1.0000
7.500 1.1039 0.03507 0.02287 -0.0557 0.3801 1.0000
7.750 1.1156 0.03601 0.02394 -0.0537 0.3722 1.0000
8.000 1.1410 0.03645 0.02433 -0.0533 0.3658 1.0000
8.250 1.1435 0.03781 0.02589 -0.0504 0.3579 1.0000
8.500 1.1676 0.03830 0.02636 -0.0498 0.3514 1.0000
8.750 1.1694 0.03972 0.02796 -0.0469 0.3440 1.0000
9.000 1.1825 0.04060 0.02890 -0.0452 0.3370 1.0000
9.250 1.1945 0.04158 0.02994 -0.0433 0.3303 1.0000
9.500 1.1911 0.04324 0.03175 -0.0401 0.3229 1.0000
9.750 1.2224 0.04338 0.03183 -0.0402 0.3168 1.0000
10.000 1.1978 0.04631 0.03502 -0.0357 0.3097 1.0000
10.250 1.2084 0.04754 0.03633 -0.0342 0.3035 1.0000
10.500 1.2197 0.04887 0.03773 -0.0329 0.2983 1.0000
10.750 1.1822 0.05358 0.04268 -0.0295 0.2916 1.0000
11.000 1.1980 0.05462 0.04377 -0.0287 0.2866 1.0000
11.250 1.1641 0.06001 0.04932 -0.0271 0.2805 1.0000
11.500 1.1073 0.06891 0.05838 -0.0273 0.2724 1.0000
11.750 1.1445 0.06746 0.05696 -0.0261 0.2696 1.0000
12.000 1.0230 0.08746 0.07706 -0.0317 0.2557 1.0000
12.250 1.0484 0.08700 0.07668 -0.0305 0.2539 1.0000
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Polar data table (+)
Polar graphs
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