GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 50,000 Max Cl/Cd: 31.83 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe650-il-50000.txt Download as CSV file: xf-goe650-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3427 0.11852 0.11138 -0.0239 1.0000 0.2760
-8.500 -0.3075 0.11211 0.10491 -0.0223 1.0000 0.2843
-8.250 -0.3269 0.11203 0.10495 -0.0201 1.0000 0.2919
-8.000 -0.3474 0.11117 0.10422 -0.0180 1.0000 0.2950
-7.750 -0.3247 0.10683 0.09985 -0.0162 1.0000 0.3032
-7.500 -0.3528 0.10728 0.10044 -0.0134 1.0000 0.3101
-7.250 -0.3563 0.10456 0.09779 -0.0115 1.0000 0.3143
-7.000 -0.3530 0.10242 0.09568 -0.0091 1.0000 0.3254
-6.750 -0.3958 0.10364 0.09707 -0.0052 1.0000 0.3290
-6.500 -0.3663 0.09863 0.09202 -0.0042 1.0000 0.3409
-6.250 -0.4050 0.09932 0.09286 0.0000 1.0000 0.3464
-6.000 -0.3882 0.09521 0.08874 0.0013 1.0000 0.3558
-5.750 -0.4175 0.09500 0.08865 0.0054 1.0000 0.3634
-5.500 -0.4205 0.09222 0.08592 0.0077 1.0000 0.3712
-5.250 -0.4810 0.07843 0.07199 -0.0144 1.0000 0.2574
-5.000 -0.4763 0.07396 0.06748 -0.0154 1.0000 0.2548
-4.750 -0.4690 0.06798 0.06135 -0.0208 1.0000 0.2544
-4.500 -0.4481 0.05781 0.05059 -0.0347 1.0000 0.2587
-4.250 -0.4432 0.06047 0.05356 -0.0257 1.0000 0.2707
-4.000 -0.4245 0.05632 0.04917 -0.0298 1.0000 0.2798
-3.750 -0.4070 0.05410 0.04681 -0.0308 1.0000 0.2889
-3.500 -0.3817 0.04991 0.04224 -0.0358 1.0000 0.2961
-3.250 -0.3660 0.04898 0.04128 -0.0346 1.0000 0.3032
-3.000 -0.3370 0.04539 0.03718 -0.0396 1.0000 0.3102
-2.750 -0.3202 0.04449 0.03627 -0.0388 1.0000 0.3169
-2.500 -0.2986 0.04301 0.03457 -0.0398 1.0000 0.3238
-2.250 -0.2753 0.04141 0.03267 -0.0414 1.0000 0.3320
-2.000 -0.2576 0.04092 0.03215 -0.0408 1.0000 0.3397
-1.750 -0.2336 0.03966 0.03052 -0.0424 1.0000 0.3488
-1.500 -0.2172 0.03946 0.03038 -0.0414 1.0000 0.3566
-1.250 -0.1960 0.03887 0.02955 -0.0419 1.0000 0.3681
-1.000 -0.1787 0.03875 0.02943 -0.0413 1.0000 0.3774
-0.750 -0.1592 0.03849 0.02905 -0.0413 1.0000 0.3889
-0.500 -0.1392 0.03843 0.02883 -0.0415 1.0000 0.4034
-0.250 -0.1225 0.03854 0.02900 -0.0407 1.0000 0.4160
0.000 -0.1049 0.03865 0.02909 -0.0403 1.0000 0.4302
0.250 -0.0371 0.04040 0.03076 -0.0483 0.9742 0.4632
0.500 0.0103 0.04136 0.03167 -0.0525 0.9570 0.4950
0.750 0.0549 0.04215 0.03244 -0.0561 0.9399 0.5296
1.000 0.0935 0.04264 0.03296 -0.0585 0.9228 0.5641
1.250 0.1322 0.04308 0.03343 -0.0608 0.9057 0.6016
1.500 0.1710 0.04343 0.03388 -0.0629 0.8892 0.6419
1.750 0.2116 0.04372 0.03426 -0.0652 0.8731 0.6892
2.000 0.2567 0.04372 0.03453 -0.0681 0.8576 0.7482
2.250 0.3091 0.04308 0.03457 -0.0728 0.8399 1.0000
2.500 0.3584 0.04391 0.03506 -0.0782 0.8220 1.0000
2.750 0.4010 0.04462 0.03552 -0.0816 0.8043 1.0000
3.000 0.4397 0.04523 0.03593 -0.0837 0.7865 1.0000
3.250 0.4762 0.04575 0.03631 -0.0851 0.7687 1.0000
3.500 0.5109 0.04619 0.03665 -0.0860 0.7506 1.0000
3.750 0.5450 0.04655 0.03694 -0.0867 0.7322 1.0000
4.000 0.5788 0.04680 0.03715 -0.0870 0.7138 1.0000
4.250 0.6129 0.04695 0.03727 -0.0872 0.6955 1.0000
4.500 0.6479 0.04692 0.03723 -0.0872 0.6774 1.0000
4.750 0.6830 0.04676 0.03706 -0.0871 0.6598 1.0000
5.000 0.7200 0.04632 0.03662 -0.0869 0.6427 1.0000
5.250 0.7926 0.04329 0.03365 -0.0888 0.6325 1.0000
5.500 0.8354 0.04203 0.03241 -0.0886 0.6162 1.0000
5.750 0.8829 0.04052 0.03095 -0.0889 0.5998 1.0000
6.000 0.9450 0.03827 0.02875 -0.0907 0.5828 1.0000
6.250 1.0117 0.03592 0.02636 -0.0932 0.5645 1.0000
6.500 1.0398 0.03590 0.02634 -0.0920 0.5437 1.0000
6.750 1.0721 0.03584 0.02624 -0.0914 0.5229 1.0000
7.000 1.1068 0.03583 0.02616 -0.0912 0.5023 1.0000
7.250 1.1389 0.03612 0.02639 -0.0908 0.4826 1.0000
7.500 1.1672 0.03667 0.02688 -0.0901 0.4638 1.0000
7.750 1.1891 0.03760 0.02778 -0.0888 0.4468 1.0000
8.000 1.2080 0.03867 0.02888 -0.0872 0.4308 1.0000
8.250 1.2257 0.03990 0.03013 -0.0855 0.4161 1.0000
8.500 1.2467 0.04107 0.03130 -0.0843 0.4024 1.0000
8.750 1.2745 0.04204 0.03221 -0.0839 0.3890 1.0000
9.000 1.2846 0.04372 0.03402 -0.0815 0.3776 1.0000
9.250 1.2888 0.04588 0.03634 -0.0787 0.3679 1.0000
9.500 1.3256 0.04681 0.03716 -0.0794 0.3565 1.0000
9.750 1.2997 0.05018 0.04088 -0.0735 0.3500 1.0000
10.000 1.3439 0.05103 0.04164 -0.0751 0.3397 1.0000
10.250 1.3003 0.05542 0.04639 -0.0680 0.3362 1.0000
10.500 1.2350 0.06134 0.05251 -0.0604 0.3343 1.0000
10.750 0.9630 0.09699 0.08809 -0.0644 0.3391 1.0000
11.000 0.9166 0.10880 0.09988 -0.0685 0.3390 1.0000
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Polar data table (+)
Polar graphs
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