GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 100,000 Max Cl/Cd: 52.73 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe758-il-100000-n5.txt Download as CSV file: xf-goe758-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1879 0.11735 0.11287 -0.0440 1.0000 0.0764
-11.000 -0.1932 0.11482 0.11039 -0.0454 0.9978 0.0789
-10.750 -0.2038 0.11115 0.10674 -0.0510 0.9894 0.0804
-10.500 -0.2054 0.10678 0.10238 -0.0557 0.9813 0.0807
-10.250 -0.1939 0.10152 0.09713 -0.0584 0.9735 0.0811
-10.000 -0.1649 0.09704 0.09261 -0.0583 0.9653 0.0826
-9.750 -0.1443 0.09327 0.08880 -0.0601 0.9570 0.0851
-9.500 -0.1324 0.08909 0.08460 -0.0631 0.9477 0.0872
-9.250 -0.1239 0.08443 0.07992 -0.0665 0.9377 0.0871
-8.750 -0.2656 0.07531 0.07062 -0.0753 0.9497 0.0499
-8.500 -0.2479 0.07140 0.06669 -0.0793 0.9379 0.0494
-8.250 -0.2376 0.06551 0.06075 -0.0867 0.9229 0.0486
-8.000 -0.2343 0.05788 0.05294 -0.0956 0.9067 0.0476
-7.750 -0.2350 0.05142 0.04616 -0.1010 0.8904 0.0470
-7.500 -0.2324 0.04637 0.04072 -0.1036 0.8750 0.0471
-7.250 -0.2250 0.04226 0.03617 -0.1047 0.8610 0.0474
-7.000 -0.2126 0.03881 0.03225 -0.1051 0.8483 0.0476
-6.750 -0.1983 0.03602 0.02905 -0.1046 0.8347 0.0474
-6.500 -0.1818 0.03357 0.02617 -0.1040 0.8216 0.0474
-6.250 -0.1626 0.03143 0.02361 -0.1034 0.8097 0.0474
-6.000 -0.1406 0.02954 0.02129 -0.1029 0.7992 0.0476
-5.750 -0.1193 0.02803 0.01943 -0.1021 0.7869 0.0481
-5.500 -0.0960 0.02674 0.01778 -0.1015 0.7759 0.0491
-5.250 -0.0708 0.02560 0.01627 -0.1010 0.7668 0.0499
-5.000 -0.0469 0.02448 0.01496 -0.1004 0.7559 0.0503
-4.750 -0.0215 0.02344 0.01378 -0.0999 0.7471 0.0507
-4.500 0.0036 0.02256 0.01279 -0.0994 0.7379 0.0512
-4.250 0.0288 0.02180 0.01193 -0.0989 0.7296 0.0519
-4.000 0.0541 0.02113 0.01118 -0.0984 0.7215 0.0526
-3.750 0.0791 0.02056 0.01053 -0.0978 0.7138 0.0535
-3.500 0.1042 0.02006 0.00994 -0.0973 0.7065 0.0549
-3.250 0.1295 0.01965 0.00942 -0.0967 0.6998 0.0570
-3.000 0.1545 0.01929 0.00896 -0.0961 0.6926 0.0591
-2.750 0.1802 0.01887 0.00845 -0.0957 0.6869 0.0611
-2.500 0.2049 0.01860 0.00813 -0.0951 0.6798 0.0635
-2.250 0.2311 0.01835 0.00775 -0.0947 0.6738 0.0668
-2.000 0.2570 0.01811 0.00746 -0.0942 0.6679 0.0720
-1.750 0.2824 0.01786 0.00724 -0.0938 0.6615 0.0851
-1.500 0.3083 0.01742 0.00696 -0.0934 0.6562 0.1418
-1.250 0.3307 0.01668 0.00696 -0.0930 0.6500 0.3313
-1.000 0.3545 0.01626 0.00704 -0.0922 0.6440 0.4760
-0.500 0.4019 0.01594 0.00717 -0.0900 0.6324 0.6644
-0.250 0.4272 0.01569 0.00719 -0.0888 0.6266 0.7635
0.250 0.5369 0.01558 0.00709 -0.0992 0.6131 1.0000
0.500 0.5617 0.01575 0.00706 -0.0986 0.6078 1.0000
0.750 0.5846 0.01596 0.00716 -0.0978 0.6018 1.0000
1.000 0.6081 0.01616 0.00725 -0.0971 0.5956 1.0000
1.250 0.6339 0.01634 0.00726 -0.0967 0.5905 1.0000
1.500 0.6565 0.01658 0.00745 -0.0958 0.5842 1.0000
1.750 0.6806 0.01678 0.00757 -0.0951 0.5781 1.0000
2.000 0.7070 0.01696 0.00761 -0.0948 0.5733 1.0000
2.250 0.7286 0.01722 0.00788 -0.0938 0.5663 1.0000
2.500 0.7533 0.01742 0.00801 -0.0932 0.5604 1.0000
2.750 0.7782 0.01763 0.00814 -0.0927 0.5549 1.0000
3.000 0.8006 0.01788 0.00840 -0.0918 0.5479 1.0000
3.250 0.8260 0.01806 0.00851 -0.0913 0.5424 1.0000
3.500 0.8485 0.01832 0.00878 -0.0905 0.5357 1.0000
3.750 0.8721 0.01854 0.00898 -0.0897 0.5292 1.0000
4.000 0.8972 0.01872 0.00912 -0.0892 0.5237 1.0000
4.250 0.9185 0.01901 0.00947 -0.0882 0.5160 1.0000
4.500 0.9435 0.01918 0.00959 -0.0877 0.5103 1.0000
4.750 0.9649 0.01949 0.00996 -0.0867 0.5030 1.0000
5.000 0.9884 0.01971 0.01018 -0.0859 0.4965 1.0000
5.250 1.0111 0.01997 0.01045 -0.0851 0.4899 1.0000
5.500 1.0330 0.02025 0.01079 -0.0842 0.4827 1.0000
5.750 1.0571 0.02046 0.01097 -0.0835 0.4768 1.0000
6.000 1.0770 0.02084 0.01143 -0.0824 0.4690 1.0000
6.250 1.1011 0.02104 0.01162 -0.0817 0.4631 1.0000
6.500 1.1203 0.02146 0.01214 -0.0804 0.4554 1.0000
6.750 1.1430 0.02174 0.01242 -0.0796 0.4491 1.0000
7.000 1.1632 0.02214 0.01290 -0.0785 0.4424 1.0000
7.250 1.1837 0.02251 0.01333 -0.0775 0.4356 1.0000
7.500 1.2055 0.02286 0.01370 -0.0766 0.4296 1.0000
7.750 1.2234 0.02335 0.01430 -0.0752 0.4224 1.0000
8.000 1.2462 0.02366 0.01461 -0.0744 0.4168 1.0000
8.250 1.2616 0.02423 0.01531 -0.0727 0.4093 1.0000
8.500 1.2814 0.02459 0.01570 -0.0715 0.4025 1.0000
8.750 1.2971 0.02514 0.01635 -0.0699 0.3955 1.0000
9.000 1.3140 0.02563 0.01692 -0.0684 0.3889 1.0000
9.250 1.3329 0.02611 0.01746 -0.0671 0.3833 1.0000
9.500 1.3438 0.02677 0.01827 -0.0648 0.3765 1.0000
9.750 1.3621 0.02719 0.01870 -0.0635 0.3705 1.0000
10.000 1.3685 0.02797 0.01963 -0.0606 0.3633 1.0000
10.250 1.3811 0.02852 0.02025 -0.0586 0.3562 1.0000
10.500 1.3861 0.02936 0.02120 -0.0558 0.3480 1.0000
10.750 1.3960 0.02997 0.02182 -0.0536 0.3392 1.0000
11.000 1.3950 0.03118 0.02318 -0.0506 0.3301 1.0000
11.250 1.4003 0.03212 0.02415 -0.0483 0.3209 1.0000
11.500 1.3997 0.03351 0.02568 -0.0459 0.3115 1.0000
11.750 1.3980 0.03507 0.02733 -0.0436 0.3012 1.0000
12.000 1.3968 0.03670 0.02899 -0.0416 0.2904 1.0000
12.250 1.3919 0.03880 0.03120 -0.0397 0.2793 1.0000
12.500 1.3849 0.04129 0.03380 -0.0382 0.2676 1.0000
12.750 1.3771 0.04405 0.03664 -0.0370 0.2552 1.0000
13.000 1.3688 0.04707 0.03973 -0.0361 0.2424 1.0000
13.250 1.3588 0.05047 0.04318 -0.0354 0.2283 1.0000
13.500 1.3481 0.05416 0.04692 -0.0351 0.2133 1.0000
13.750 1.3361 0.05815 0.05094 -0.0350 0.1966 1.0000
14.000 1.3221 0.06255 0.05533 -0.0351 0.1781 1.0000
14.250 1.3070 0.06726 0.06000 -0.0354 0.1578 1.0000
14.500 1.2880 0.07268 0.06533 -0.0361 0.1359 1.0000
14.750 1.2699 0.07823 0.07081 -0.0370 0.1181 1.0000
15.000 1.2500 0.08428 0.07679 -0.0383 0.1039 1.0000
15.250 1.2327 0.09022 0.08271 -0.0398 0.0938 1.0000
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