GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 565 AIRFOIL (goe565-il) Reynolds number: 500,000 Max Cl/Cd: 80.67 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe565-il-500000-n5.txt Download as CSV file: xf-goe565-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 565 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.8329 0.03729 0.03454 -0.0684 1.0000 0.0069
-11.000 -0.8432 0.03266 0.02958 -0.0678 1.0000 0.0070
-10.750 -0.8431 0.02971 0.02636 -0.0662 1.0000 0.0071
-10.500 -0.8294 0.02717 0.02354 -0.0664 0.9989 0.0074
-10.250 -0.8028 0.02491 0.02097 -0.0685 0.9961 0.0077
-10.000 -0.7755 0.02313 0.01891 -0.0702 0.9934 0.0079
-9.750 -0.7504 0.02115 0.01670 -0.0714 0.9902 0.0085
-9.500 -0.7228 0.01985 0.01522 -0.0725 0.9880 0.0089
-9.250 -0.6939 0.01870 0.01389 -0.0736 0.9863 0.0094
-9.000 -0.6674 0.01773 0.01273 -0.0740 0.9834 0.0099
-8.750 -0.6394 0.01682 0.01165 -0.0746 0.9809 0.0105
-8.500 -0.6100 0.01603 0.01068 -0.0754 0.9790 0.0111
-8.250 -0.5799 0.01511 0.00964 -0.0764 0.9774 0.0122
-8.000 -0.5518 0.01445 0.00890 -0.0768 0.9747 0.0137
-7.750 -0.5231 0.01387 0.00821 -0.0772 0.9719 0.0152
-7.500 -0.4927 0.01333 0.00760 -0.0780 0.9700 0.0176
-7.250 -0.4615 0.01293 0.00715 -0.0789 0.9683 0.0204
-7.000 -0.4296 0.01268 0.00690 -0.0798 0.9667 0.0235
-6.750 -0.4019 0.01254 0.00671 -0.0798 0.9626 0.0267
-6.500 -0.3716 0.01228 0.00639 -0.0804 0.9598 0.0289
-6.250 -0.3400 0.01216 0.00626 -0.0812 0.9576 0.0310
-6.000 -0.3098 0.01206 0.00613 -0.0817 0.9548 0.0332
-5.750 -0.2816 0.01190 0.00590 -0.0818 0.9506 0.0349
-5.500 -0.2512 0.01178 0.00572 -0.0823 0.9473 0.0360
-5.250 -0.2219 0.01124 0.00515 -0.0827 0.9442 0.0382
-5.000 -0.1950 0.01108 0.00498 -0.0825 0.9390 0.0401
-4.750 -0.1661 0.01082 0.00467 -0.0827 0.9351 0.0416
-4.500 -0.1376 0.01050 0.00430 -0.0828 0.9305 0.0426
-4.250 -0.1107 0.01021 0.00395 -0.0825 0.9235 0.0436
-4.000 -0.0822 0.00994 0.00362 -0.0825 0.9175 0.0446
-3.750 -0.0555 0.00973 0.00336 -0.0822 0.9095 0.0454
-3.500 -0.0276 0.00957 0.00314 -0.0820 0.9022 0.0462
-3.250 -0.0013 0.00920 0.00273 -0.0816 0.8937 0.0482
-3.000 0.0259 0.00897 0.00246 -0.0814 0.8868 0.0500
-2.750 0.0529 0.00878 0.00225 -0.0811 0.8791 0.0518
-2.500 0.0802 0.00863 0.00206 -0.0809 0.8715 0.0538
-2.250 0.1074 0.00850 0.00189 -0.0806 0.8620 0.0558
-2.000 0.1341 0.00839 0.00172 -0.0801 0.8480 0.0579
-1.750 0.1607 0.00830 0.00156 -0.0796 0.8298 0.0613
-1.500 0.1868 0.00819 0.00143 -0.0791 0.8089 0.0696
-1.250 0.2130 0.00807 0.00135 -0.0786 0.7909 0.0979
-1.000 0.2395 0.00798 0.00126 -0.0782 0.7765 0.1177
-0.750 0.2657 0.00784 0.00119 -0.0778 0.7629 0.1501
-0.500 0.2909 0.00757 0.00117 -0.0774 0.7487 0.2529
0.000 0.3429 0.00745 0.00115 -0.0764 0.7174 0.3294
0.250 0.3679 0.00731 0.00116 -0.0759 0.6994 0.3970
0.500 0.3922 0.00709 0.00121 -0.0752 0.6816 0.5033
0.750 0.4168 0.00697 0.00127 -0.0744 0.6637 0.5823
1.000 0.4415 0.00690 0.00132 -0.0737 0.6433 0.6441
1.250 0.4654 0.00688 0.00136 -0.0727 0.6167 0.6951
1.750 0.5437 0.00674 0.00155 -0.0774 0.5348 1.0000
2.000 0.5660 0.00703 0.00166 -0.0763 0.4985 1.0000
2.250 0.5883 0.00736 0.00179 -0.0751 0.4554 1.0000
2.500 0.6101 0.00775 0.00193 -0.0740 0.4025 1.0000
2.750 0.6329 0.00809 0.00208 -0.0730 0.3621 1.0000
3.000 0.6565 0.00838 0.00223 -0.0721 0.3330 1.0000
3.250 0.6805 0.00866 0.00240 -0.0714 0.3062 1.0000
3.500 0.7041 0.00898 0.00258 -0.0706 0.2749 1.0000
3.750 0.7270 0.00937 0.00278 -0.0697 0.2335 1.0000
4.000 0.7497 0.00980 0.00302 -0.0688 0.1950 1.0000
4.250 0.7737 0.01010 0.00324 -0.0681 0.1781 1.0000
4.500 0.7982 0.01036 0.00347 -0.0674 0.1672 1.0000
4.750 0.8223 0.01066 0.00371 -0.0667 0.1546 1.0000
5.000 0.8468 0.01092 0.00395 -0.0661 0.1439 1.0000
5.250 0.8714 0.01116 0.00419 -0.0655 0.1333 1.0000
5.500 0.8951 0.01150 0.00445 -0.0648 0.1132 1.0000
5.750 0.9164 0.01209 0.00483 -0.0637 0.0774 1.0000
6.000 0.9373 0.01271 0.00530 -0.0626 0.0476 1.0000
6.250 0.9600 0.01316 0.00571 -0.0617 0.0390 1.0000
6.500 0.9834 0.01352 0.00610 -0.0609 0.0359 1.0000
6.750 1.0061 0.01395 0.00653 -0.0600 0.0329 1.0000
7.000 1.0283 0.01443 0.00706 -0.0591 0.0299 1.0000
7.250 1.0515 0.01478 0.00746 -0.0583 0.0285 1.0000
7.500 1.0745 0.01513 0.00787 -0.0575 0.0267 1.0000
7.750 1.0969 0.01554 0.00832 -0.0566 0.0245 1.0000
8.000 1.1181 0.01606 0.00886 -0.0556 0.0220 1.0000
8.250 1.1395 0.01654 0.00939 -0.0545 0.0201 1.0000
8.500 1.1615 0.01694 0.00986 -0.0536 0.0183 1.0000
8.750 1.1827 0.01740 0.01033 -0.0526 0.0160 1.0000
9.000 1.2023 0.01800 0.01095 -0.0514 0.0143 1.0000
9.250 1.2222 0.01854 0.01155 -0.0502 0.0131 1.0000
9.500 1.2412 0.01912 0.01219 -0.0488 0.0121 1.0000
9.750 1.2592 0.01978 0.01287 -0.0474 0.0110 1.0000
10.000 1.2749 0.02060 0.01375 -0.0456 0.0102 1.0000
10.250 1.2915 0.02127 0.01454 -0.0440 0.0096 1.0000
10.500 1.3064 0.02194 0.01529 -0.0420 0.0090 1.0000
10.750 1.3191 0.02270 0.01613 -0.0398 0.0086 1.0000
11.000 1.3311 0.02349 0.01700 -0.0375 0.0081 1.0000
11.250 1.3414 0.02440 0.01798 -0.0351 0.0077 1.0000
11.500 1.3467 0.02567 0.01935 -0.0322 0.0073 1.0000
11.750 1.3555 0.02670 0.02049 -0.0299 0.0071 1.0000
12.000 1.3637 0.02781 0.02172 -0.0276 0.0069 1.0000
12.250 1.3696 0.02911 0.02316 -0.0253 0.0068 1.0000
12.500 1.3749 0.03050 0.02468 -0.0231 0.0066 1.0000
12.750 1.3798 0.03197 0.02627 -0.0212 0.0064 1.0000
13.000 1.3834 0.03361 0.02803 -0.0193 0.0062 1.0000
13.250 1.3877 0.03525 0.02978 -0.0178 0.0060 1.0000
13.500 1.3920 0.03697 0.03160 -0.0165 0.0058 1.0000
13.750 1.3927 0.03911 0.03387 -0.0152 0.0056 1.0000
14.000 1.3880 0.04195 0.03686 -0.0142 0.0056 1.0000
14.250 1.3872 0.04454 0.03955 -0.0137 0.0054 1.0000
14.500 1.3813 0.04789 0.04304 -0.0136 0.0053 1.0000
14.750 1.3734 0.05171 0.04700 -0.0139 0.0052 1.0000
15.000 1.3614 0.05637 0.05181 -0.0149 0.0052 1.0000
15.250 1.3507 0.06122 0.05682 -0.0164 0.0051 1.0000
15.500 1.3416 0.06618 0.06195 -0.0184 0.0051 1.0000
15.750 1.3319 0.07158 0.06752 -0.0208 0.0050 1.0000
16.000 1.3155 0.07834 0.07443 -0.0241 0.0051 1.0000
16.250 1.3020 0.08501 0.08129 -0.0276 0.0050 1.0000
16.500 1.2829 0.09295 0.08938 -0.0318 0.0050 1.0000
16.750 1.2669 0.10058 0.09717 -0.0360 0.0050 1.0000
17.000 1.2476 0.10906 0.10579 -0.0406 0.0050 1.0000
17.250 1.2293 0.11765 0.11450 -0.0455 0.0050 1.0000
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