GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 50,000 Max Cl/Cd: 22.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe290-il-50000-n5.txt Download as CSV file: xf-goe290-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 290 (MVA 290) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3522 0.10328 0.09561 -0.0472 1.0000 0.0949
-10.500 -0.3613 0.09797 0.09037 -0.0495 1.0000 0.0947
-10.250 -0.3753 0.09194 0.08442 -0.0522 1.0000 0.0943
-10.000 -0.4053 0.08332 0.07587 -0.0567 1.0000 0.0936
-9.750 -0.4987 0.07016 0.06270 -0.0639 1.0000 0.0915
-9.500 -0.5639 0.06494 0.05739 -0.0610 1.0000 0.0906
-9.250 -0.5990 0.06156 0.05388 -0.0577 1.0000 0.0904
-9.000 -0.5982 0.05761 0.04967 -0.0593 0.9911 0.0911
-8.750 -0.5769 0.05374 0.04548 -0.0632 0.9767 0.0928
-8.500 -0.5550 0.05007 0.04140 -0.0665 0.9617 0.0951
-8.250 -0.5325 0.04651 0.03729 -0.0693 0.9463 0.0974
-7.750 -0.4738 0.04169 0.03194 -0.0733 0.9151 0.1016
-7.500 -0.4441 0.03995 0.03004 -0.0747 0.8983 0.1047
-7.250 -0.4149 0.03811 0.02786 -0.0757 0.8816 0.1084
-7.000 -0.3841 0.03640 0.02590 -0.0768 0.8658 0.1116
-6.750 -0.3523 0.03509 0.02455 -0.0778 0.8506 0.1154
-6.500 -0.3209 0.03380 0.02299 -0.0785 0.8362 0.1204
-6.250 -0.2911 0.03260 0.02164 -0.0788 0.8215 0.1250
-6.000 -0.2639 0.03168 0.02065 -0.0788 0.8061 0.1304
-5.750 -0.2367 0.03083 0.01951 -0.0786 0.7916 0.1368
-5.500 -0.2104 0.02995 0.01866 -0.0783 0.7786 0.1432
-5.250 -0.1846 0.02925 0.01776 -0.0778 0.7654 0.1518
-5.000 -0.1610 0.02853 0.01709 -0.0773 0.7527 0.1605
-4.750 -0.1351 0.02780 0.01630 -0.0769 0.7429 0.1728
-4.500 -0.1121 0.02719 0.01580 -0.0764 0.7311 0.1887
-4.250 -0.0871 0.02655 0.01532 -0.0760 0.7222 0.2156
-4.000 -0.0642 0.02619 0.01526 -0.0754 0.7120 0.2630
-3.750 -0.0385 0.02603 0.01507 -0.0748 0.7047 0.3225
-3.500 -0.0156 0.02610 0.01514 -0.0741 0.6954 0.3639
-3.250 0.0098 0.02609 0.01505 -0.0735 0.6885 0.3973
-3.000 0.0348 0.02613 0.01502 -0.0730 0.6812 0.4250
-2.750 0.0594 0.02615 0.01505 -0.0723 0.6739 0.4506
-2.500 0.0850 0.02613 0.01499 -0.0716 0.6683 0.4839
-2.250 0.1073 0.02623 0.01525 -0.0705 0.6618 0.5177
-2.000 0.1308 0.02630 0.01540 -0.0695 0.6555 0.5494
-1.750 0.1570 0.02626 0.01537 -0.0689 0.6505 0.5747
-1.500 0.1834 0.02626 0.01535 -0.0685 0.6453 0.5949
-1.250 0.2078 0.02638 0.01551 -0.0682 0.6390 0.6137
-1.000 0.2341 0.02640 0.01555 -0.0678 0.6339 0.6356
-0.750 0.2614 0.02635 0.01552 -0.0673 0.6299 0.6628
-0.500 0.2849 0.02653 0.01584 -0.0665 0.6248 0.6960
-0.250 0.3081 0.02675 0.01622 -0.0655 0.6191 0.7387
0.000 0.3372 0.02686 0.01645 -0.0651 0.6144 0.7968
0.250 0.3799 0.02696 0.01653 -0.0671 0.6105 0.8673
0.500 0.4262 0.02745 0.01699 -0.0709 0.6052 0.9351
0.750 0.4785 0.02795 0.01740 -0.0765 0.5992 0.9901
1.000 0.5066 0.02830 0.01757 -0.0773 0.5946 1.0000
1.250 0.5293 0.02859 0.01766 -0.0766 0.5910 1.0000
1.500 0.5442 0.02936 0.01837 -0.0753 0.5859 1.0000
1.750 0.5591 0.03017 0.01913 -0.0739 0.5802 1.0000
2.000 0.5807 0.03066 0.01950 -0.0731 0.5754 1.0000
2.250 0.6080 0.03085 0.01953 -0.0728 0.5713 1.0000
2.500 0.6193 0.03189 0.02058 -0.0710 0.5638 1.0000
2.750 0.6405 0.03229 0.02090 -0.0700 0.5564 1.0000
3.000 0.6737 0.03202 0.02043 -0.0701 0.5509 1.0000
3.250 0.6811 0.03315 0.02161 -0.0678 0.5407 1.0000
3.500 0.7093 0.03312 0.02146 -0.0673 0.5340 1.0000
3.750 0.7303 0.03358 0.02186 -0.0663 0.5271 1.0000
4.000 0.7429 0.03456 0.02287 -0.0647 0.5190 1.0000
4.250 0.7706 0.03472 0.02296 -0.0644 0.5139 1.0000
4.500 0.7909 0.03535 0.02357 -0.0635 0.5081 1.0000
4.750 0.7971 0.03674 0.02505 -0.0613 0.4996 1.0000
5.000 0.8249 0.03690 0.02516 -0.0610 0.4944 1.0000
5.250 0.8434 0.03764 0.02590 -0.0599 0.4884 1.0000
5.500 0.8441 0.03937 0.02774 -0.0574 0.4793 1.0000
5.750 0.8740 0.03939 0.02772 -0.0572 0.4746 1.0000
6.000 0.8695 0.04145 0.02989 -0.0543 0.4652 1.0000
6.250 0.8847 0.04227 0.03074 -0.0530 0.4581 1.0000
6.500 0.9218 0.04178 0.03019 -0.0533 0.4542 1.0000
6.750 0.8870 0.04556 0.03412 -0.0482 0.4410 1.0000
7.000 0.9229 0.04505 0.03359 -0.0483 0.4369 1.0000
7.500 0.9174 0.04913 0.03777 -0.0438 0.4193 1.0000
8.000 0.8605 0.05994 0.04874 -0.0415 0.3916 1.0000
8.250 0.8790 0.06075 0.04957 -0.0408 0.3871 1.0000
8.500 0.9071 0.06046 0.04929 -0.0400 0.3847 1.0000
9.000 0.8505 0.07426 0.06319 -0.0412 0.3599 1.0000
9.250 0.8629 0.07601 0.06498 -0.0408 0.3555 1.0000
9.500 0.8847 0.07651 0.06550 -0.0402 0.3531 1.0000
10.000 0.8572 0.08758 0.07668 -0.0417 0.3395 1.0000
10.250 0.8749 0.08888 0.07802 -0.0413 0.3375 1.0000
10.500 0.8375 0.09791 0.08711 -0.0434 0.3296 1.0000
10.750 0.8439 0.10069 0.08994 -0.0436 0.3256 1.0000
11.000 0.8624 0.10176 0.09108 -0.0432 0.3228 1.0000
11.250 0.8526 0.10694 0.09632 -0.0442 0.3181 1.0000
11.500 0.8434 0.11189 0.10134 -0.0453 0.3126 1.0000
11.750 0.8611 0.11292 0.10242 -0.0449 0.3086 1.0000
12.000 0.8853 0.11291 0.10247 -0.0441 0.3053 1.0000
12.250 0.8644 0.11906 0.10869 -0.0458 0.2959 1.0000
12.500 0.8879 0.11903 0.10872 -0.0449 0.2920 1.0000
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Polar data table (+)
Polar graphs
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