GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 200,000 Max Cl/Cd: 68.97 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe290-il-200000.txt Download as CSV file: xf-goe290-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3310 0.10770 0.10396 -0.0408 1.0000 0.0979
-10.750 -0.7104 0.05413 0.04952 -0.0669 1.0000 0.0680
-10.500 -0.7131 0.05238 0.04780 -0.0640 1.0000 0.0684
-10.250 -0.7061 0.05100 0.04647 -0.0624 0.9990 0.0690
-9.750 -0.6852 0.03912 0.03310 -0.0694 0.9821 0.0679
-9.500 -0.6526 0.03647 0.03036 -0.0720 0.9750 0.0687
-9.250 -0.6128 0.03467 0.02853 -0.0754 0.9699 0.0700
-9.000 -0.5793 0.03276 0.02644 -0.0777 0.9611 0.0714
-8.750 -0.5450 0.03066 0.02404 -0.0800 0.9533 0.0728
-8.500 -0.5176 0.02886 0.02194 -0.0805 0.9392 0.0739
-8.250 -0.4918 0.02744 0.02019 -0.0803 0.9222 0.0750
-8.000 -0.4681 0.02582 0.01837 -0.0797 0.9002 0.0762
-7.750 -0.4417 0.02452 0.01706 -0.0794 0.8773 0.0779
-7.500 -0.4157 0.02362 0.01603 -0.0787 0.8527 0.0799
-7.250 -0.3916 0.02282 0.01501 -0.0777 0.8248 0.0819
-7.000 -0.3676 0.02217 0.01404 -0.0766 0.7982 0.0837
-6.750 -0.3434 0.02124 0.01290 -0.0758 0.7730 0.0856
-6.500 -0.3187 0.02049 0.01211 -0.0752 0.7499 0.0881
-6.250 -0.2933 0.02000 0.01149 -0.0747 0.7297 0.0912
-6.000 -0.2674 0.01959 0.01087 -0.0741 0.7123 0.0942
-5.750 -0.2423 0.01878 0.01001 -0.0737 0.6979 0.0974
-5.500 -0.2164 0.01830 0.00950 -0.0733 0.6842 0.1011
-5.250 -0.1897 0.01797 0.00904 -0.0730 0.6727 0.1054
-5.000 -0.1643 0.01740 0.00845 -0.0726 0.6634 0.1101
-4.750 -0.1375 0.01707 0.00810 -0.0724 0.6544 0.1156
-4.500 -0.1113 0.01666 0.00766 -0.0722 0.6467 0.1218
-4.250 -0.0843 0.01640 0.00736 -0.0720 0.6397 0.1295
-4.000 -0.0578 0.01600 0.00701 -0.0718 0.6324 0.1392
-3.750 -0.0312 0.01565 0.00665 -0.0716 0.6264 0.1536
-3.500 -0.0055 0.01506 0.00628 -0.0715 0.6209 0.1906
-3.250 0.0197 0.01459 0.00637 -0.0713 0.6154 0.3231
-3.000 0.0478 0.01468 0.00645 -0.0713 0.6104 0.3616
-2.750 0.0761 0.01481 0.00650 -0.0712 0.6059 0.3850
-2.500 0.1044 0.01486 0.00655 -0.0713 0.6011 0.4030
-2.250 0.1327 0.01489 0.00657 -0.0713 0.5961 0.4187
-2.000 0.1614 0.01494 0.00657 -0.0714 0.5917 0.4336
-1.750 0.1897 0.01498 0.00659 -0.0714 0.5878 0.4486
-1.500 0.2179 0.01502 0.00666 -0.0714 0.5837 0.4641
-1.250 0.2460 0.01499 0.00669 -0.0715 0.5790 0.4796
-1.000 0.2741 0.01498 0.00670 -0.0715 0.5741 0.4963
-0.750 0.3024 0.01497 0.00669 -0.0714 0.5695 0.5149
-0.500 0.3303 0.01501 0.00677 -0.0714 0.5652 0.5355
-0.250 0.3574 0.01491 0.00685 -0.0713 0.5605 0.5610
0.000 0.3846 0.01482 0.00691 -0.0711 0.5561 0.5955
0.250 0.4108 0.01467 0.00699 -0.0706 0.5524 0.6462
0.500 0.4348 0.01450 0.00714 -0.0694 0.5491 0.7354
0.750 0.4571 0.01440 0.00742 -0.0673 0.5452 0.8532
1.000 0.4951 0.01448 0.00761 -0.0686 0.5404 0.9346
1.250 0.5446 0.01465 0.00772 -0.0728 0.5359 0.9723
1.500 0.5984 0.01483 0.00776 -0.0780 0.5312 0.9926
1.750 0.6405 0.01503 0.00787 -0.0811 0.5265 1.0000
2.000 0.6624 0.01513 0.00798 -0.0802 0.5217 1.0000
2.250 0.6856 0.01525 0.00804 -0.0794 0.5172 1.0000
2.500 0.7100 0.01540 0.00811 -0.0789 0.5134 1.0000
2.750 0.7354 0.01565 0.00822 -0.0784 0.5099 1.0000
3.000 0.7584 0.01583 0.00845 -0.0776 0.5057 1.0000
3.250 0.7821 0.01599 0.00863 -0.0769 0.5011 1.0000
3.500 0.8071 0.01613 0.00873 -0.0764 0.4969 1.0000
3.750 0.8334 0.01630 0.00881 -0.0761 0.4931 1.0000
4.000 0.8592 0.01655 0.00902 -0.0758 0.4892 1.0000
4.250 0.8828 0.01669 0.00924 -0.0751 0.4838 1.0000
4.500 0.9084 0.01678 0.00932 -0.0747 0.4786 1.0000
4.750 0.9357 0.01688 0.00933 -0.0745 0.4740 1.0000
5.000 0.9606 0.01706 0.00953 -0.0740 0.4689 1.0000
5.250 0.9850 0.01717 0.00970 -0.0734 0.4629 1.0000
5.500 1.0115 0.01723 0.00973 -0.0732 0.4577 1.0000
5.750 1.0379 0.01735 0.00979 -0.0729 0.4524 1.0000
6.000 1.0609 0.01739 0.00994 -0.0721 0.4446 1.0000
6.250 1.0870 0.01733 0.00979 -0.0717 0.4378 1.0000
6.500 1.1096 0.01738 0.00993 -0.0708 0.4290 1.0000
6.750 1.1341 0.01734 0.00985 -0.0701 0.4209 1.0000
7.000 1.1564 0.01744 0.01001 -0.0692 0.4113 1.0000
7.250 1.1798 0.01747 0.00997 -0.0684 0.4024 1.0000
7.500 1.2008 0.01761 0.01020 -0.0673 0.3907 1.0000
7.750 1.2222 0.01779 0.01039 -0.0663 0.3799 1.0000
8.000 1.2428 0.01802 0.01055 -0.0651 0.3694 1.0000
8.250 1.2624 0.01832 0.01088 -0.0639 0.3571 1.0000
8.500 1.2810 0.01869 0.01125 -0.0626 0.3455 1.0000
8.750 1.2981 0.01911 0.01162 -0.0610 0.3343 1.0000
9.000 1.3137 0.01960 0.01206 -0.0592 0.3231 1.0000
9.250 1.3291 0.02012 0.01259 -0.0575 0.3130 1.0000
9.500 1.3408 0.02070 0.01311 -0.0551 0.3050 1.0000
9.750 1.3540 0.02129 0.01374 -0.0531 0.2973 1.0000
10.000 1.3652 0.02200 0.01440 -0.0509 0.2910 1.0000
10.250 1.3785 0.02268 0.01515 -0.0491 0.2844 1.0000
10.500 1.3888 0.02351 0.01597 -0.0471 0.2776 1.0000
10.750 1.4000 0.02438 0.01685 -0.0454 0.2717 1.0000
11.000 1.4108 0.02529 0.01782 -0.0437 0.2655 1.0000
11.250 1.4190 0.02639 0.01890 -0.0419 0.2599 1.0000
11.500 1.4297 0.02743 0.02003 -0.0405 0.2543 1.0000
11.750 1.4377 0.02867 0.02132 -0.0391 0.2483 1.0000
12.000 1.4437 0.03013 0.02276 -0.0376 0.2427 1.0000
12.250 1.4523 0.03150 0.02427 -0.0367 0.2370 1.0000
12.500 1.4574 0.03318 0.02598 -0.0355 0.2313 1.0000
12.750 1.4622 0.03495 0.02780 -0.0346 0.2259 1.0000
13.000 1.4660 0.03693 0.02989 -0.0338 0.2190 1.0000
13.250 1.4662 0.03923 0.03218 -0.0330 0.2131 1.0000
13.500 1.4704 0.04138 0.03449 -0.0326 0.2066 1.0000
13.750 1.4691 0.04404 0.03720 -0.0322 0.1999 1.0000
14.000 1.4690 0.04677 0.04004 -0.0320 0.1916 1.0000
14.250 1.4648 0.04998 0.04331 -0.0320 0.1828 1.0000
14.500 1.4621 0.05319 0.04661 -0.0321 0.1690 1.0000
14.750 1.4448 0.05810 0.05145 -0.0325 0.1384 1.0000
15.000 1.4179 0.06426 0.05746 -0.0330 0.1216 1.0000
15.250 1.3976 0.06970 0.06287 -0.0335 0.1122 1.0000
15.500 1.3816 0.07478 0.06797 -0.0341 0.1042 1.0000
15.750 1.3678 0.07969 0.07294 -0.0347 0.0969 1.0000
16.000 1.3542 0.08469 0.07798 -0.0355 0.0898 1.0000
16.250 1.3443 0.08931 0.08268 -0.0363 0.0799 1.0000
16.500 1.3308 0.09452 0.08792 -0.0374 0.0696 1.0000
16.750 1.3156 0.10007 0.09348 -0.0387 0.0639 1.0000
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