GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 50,000 Max Cl/Cd: 28.72 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe645-il-50000-n5.txt Download as CSV file: xf-goe645-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2888 0.10498 0.09776 -0.0452 1.0000 0.0855
-10.250 -0.2915 0.10177 0.09463 -0.0456 1.0000 0.0867
-10.000 -0.2975 0.09829 0.09125 -0.0462 1.0000 0.0877
-9.750 -0.3068 0.09464 0.08771 -0.0466 1.0000 0.0886
-9.500 -0.3196 0.09090 0.08409 -0.0469 1.0000 0.0890
-9.250 -0.3377 0.08717 0.08051 -0.0467 1.0000 0.0893
-9.000 -0.3624 0.08374 0.07725 -0.0458 1.0000 0.0893
-8.750 -0.3954 0.08082 0.07451 -0.0437 1.0000 0.0891
-8.500 -0.4268 0.07426 0.06805 -0.0478 0.9918 0.0892
-8.250 -0.4681 0.05543 0.04869 -0.0683 0.9677 0.0901
-8.000 -0.4706 0.04711 0.03961 -0.0754 0.9513 0.0931
-7.750 -0.4365 0.04581 0.03832 -0.0779 0.9419 0.0969
-7.500 -0.4172 0.04240 0.03448 -0.0803 0.9289 0.1011
-7.250 -0.3959 0.03902 0.03054 -0.0824 0.9170 0.1058
-7.000 -0.3589 0.03778 0.02931 -0.0848 0.9090 0.1123
-6.750 -0.3355 0.03553 0.02662 -0.0857 0.8965 0.1200
-6.500 -0.3026 0.03448 0.02559 -0.0871 0.8870 0.1284
-6.250 -0.2706 0.03328 0.02429 -0.0885 0.8769 0.1397
-6.000 -0.2424 0.03239 0.02330 -0.0889 0.8656 0.1526
-5.750 -0.2065 0.03179 0.02262 -0.0904 0.8568 0.1680
-5.500 -0.1805 0.03146 0.02218 -0.0901 0.8442 0.1820
-5.250 -0.1478 0.03114 0.02173 -0.0908 0.8345 0.1972
-5.000 -0.1187 0.03108 0.02157 -0.0909 0.8230 0.2130
-4.750 -0.0918 0.03116 0.02157 -0.0905 0.8112 0.2293
-4.500 -0.0586 0.03068 0.02084 -0.0912 0.8022 0.2445
-4.250 -0.0342 0.03046 0.02062 -0.0903 0.7894 0.2528
-4.000 -0.0045 0.02975 0.01963 -0.0905 0.7793 0.2640
-3.750 0.0238 0.02929 0.01905 -0.0903 0.7684 0.2733
-3.500 0.0498 0.02886 0.01846 -0.0899 0.7569 0.2839
-3.250 0.0817 0.02838 0.01770 -0.0902 0.7477 0.2978
-3.000 0.1048 0.02823 0.01756 -0.0892 0.7353 0.3075
-2.750 0.1348 0.02786 0.01700 -0.0893 0.7261 0.3199
-2.500 0.1605 0.02766 0.01666 -0.0887 0.7147 0.3316
-2.250 0.1869 0.02749 0.01643 -0.0882 0.7042 0.3431
-2.000 0.2153 0.02728 0.01608 -0.0880 0.6947 0.3565
-1.750 0.2391 0.02728 0.01595 -0.0872 0.6838 0.3707
-1.500 0.2687 0.02708 0.01570 -0.0870 0.6753 0.3865
-1.250 0.2910 0.02715 0.01576 -0.0860 0.6641 0.4011
-1.000 0.3221 0.02693 0.01546 -0.0861 0.6565 0.4177
-0.750 0.3440 0.02704 0.01555 -0.0852 0.6453 0.4306
-0.500 0.3760 0.02681 0.01519 -0.0854 0.6380 0.4451
-0.250 0.3975 0.02697 0.01538 -0.0844 0.6272 0.4579
0.000 0.4282 0.02677 0.01512 -0.0844 0.6198 0.4729
0.250 0.4498 0.02692 0.01533 -0.0835 0.6094 0.4880
0.500 0.4795 0.02675 0.01514 -0.0833 0.6021 0.5077
0.750 0.5007 0.02690 0.01538 -0.0823 0.5919 0.5288
1.000 0.5294 0.02666 0.01520 -0.0819 0.5845 0.5594
1.250 0.5493 0.02670 0.01547 -0.0806 0.5746 0.6008
1.500 0.5778 0.02604 0.01532 -0.0796 0.5673 0.7083
1.750 0.6290 0.02604 0.01545 -0.0840 0.5556 1.0000
2.000 0.6537 0.02634 0.01553 -0.0834 0.5472 1.0000
2.250 0.6766 0.02671 0.01572 -0.0825 0.5381 1.0000
2.500 0.7008 0.02704 0.01589 -0.0818 0.5301 1.0000
2.750 0.7222 0.02748 0.01621 -0.0807 0.5212 1.0000
3.000 0.7478 0.02778 0.01634 -0.0801 0.5139 1.0000
3.250 0.7662 0.02837 0.01689 -0.0788 0.5049 1.0000
3.500 0.7960 0.02851 0.01683 -0.0787 0.4988 1.0000
3.750 0.8088 0.02938 0.01775 -0.0767 0.4894 1.0000
4.000 0.8360 0.02965 0.01788 -0.0763 0.4829 1.0000
4.250 0.8515 0.03045 0.01870 -0.0747 0.4748 1.0000
4.500 0.8737 0.03096 0.01914 -0.0738 0.4677 1.0000
4.750 0.8980 0.03141 0.01952 -0.0731 0.4616 1.0000
5.000 0.9101 0.03239 0.02056 -0.0712 0.4533 1.0000
5.250 0.9376 0.03268 0.02075 -0.0709 0.4476 1.0000
5.500 0.9480 0.03378 0.02192 -0.0688 0.4398 1.0000
5.750 0.9671 0.03445 0.02257 -0.0676 0.4330 1.0000
6.000 0.9959 0.03468 0.02270 -0.0675 0.4278 1.0000
6.250 0.9957 0.03629 0.02448 -0.0644 0.4195 1.0000
6.500 1.0200 0.03670 0.02484 -0.0638 0.4138 1.0000
6.750 1.0335 0.03771 0.02588 -0.0622 0.4078 1.0000
7.000 1.0356 0.03923 0.02749 -0.0595 0.4006 1.0000
7.250 1.0647 0.03936 0.02756 -0.0593 0.3956 1.0000
7.500 1.0568 0.04133 0.02965 -0.0557 0.3887 1.0000
7.750 1.0592 0.04276 0.03113 -0.0531 0.3823 1.0000
8.000 1.1004 0.04212 0.03040 -0.0538 0.3775 1.0000
8.250 1.0526 0.04669 0.03518 -0.0480 0.3696 1.0000
8.500 1.0661 0.04765 0.03616 -0.0468 0.3642 1.0000
8.750 1.1117 0.04650 0.03495 -0.0472 0.3607 1.0000
9.000 1.0065 0.05774 0.04648 -0.0433 0.3494 1.0000
9.250 1.0425 0.05661 0.04534 -0.0424 0.3463 1.0000
9.750 0.9900 0.06824 0.05714 -0.0423 0.3302 1.0000
10.250 0.9569 0.07919 0.06822 -0.0437 0.3144 1.0000
10.500 0.9217 0.08752 0.07662 -0.0457 0.3026 1.0000
10.750 0.9473 0.08692 0.07605 -0.0445 0.2991 1.0000
11.000 0.9781 0.08550 0.07466 -0.0429 0.2970 1.0000
11.500 0.9401 0.09799 0.08730 -0.0459 0.2787 1.0000
12.000 0.9528 0.10268 0.09211 -0.0460 0.2665 1.0000
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Polar data table (+)
Polar graphs
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