FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-140 (fx84w140-il) Reynolds number: 200,000 Max Cl/Cd: 79.28 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w140-il-200000.txt Download as CSV file: xf-fx84w140-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-140
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1807 0.09217 0.08871 -0.0855 0.9643 0.0667
-9.750 -0.1966 0.08404 0.08059 -0.1019 0.9524 0.0705
-9.500 -0.1918 0.07791 0.07446 -0.1054 0.9453 0.0714
-9.250 -0.1676 0.07666 0.07318 -0.1022 0.9401 0.0728
-9.000 -0.1546 0.07445 0.07094 -0.1022 0.9318 0.0746
-8.750 -0.1528 0.07149 0.06797 -0.1034 0.9215 0.0763
-8.500 -0.2994 0.04769 0.04344 -0.1168 0.8937 0.0508
-8.250 -0.2915 0.04473 0.04038 -0.1157 0.8866 0.0486
-8.000 -0.2941 0.04077 0.03612 -0.1145 0.8795 0.0476
-7.750 -0.2942 0.03686 0.03176 -0.1129 0.8716 0.0478
-7.500 -0.2879 0.03344 0.02782 -0.1111 0.8667 0.0483
-7.250 -0.2769 0.03069 0.02459 -0.1097 0.8589 0.0489
-7.000 -0.2606 0.02857 0.02194 -0.1083 0.8538 0.0498
-6.750 -0.2424 0.02606 0.01916 -0.1074 0.8497 0.0513
-6.500 -0.2202 0.02536 0.01846 -0.1070 0.8430 0.0538
-6.250 -0.1969 0.02433 0.01721 -0.1062 0.8383 0.0566
-6.000 -0.1727 0.02318 0.01571 -0.1053 0.8349 0.0589
-5.750 -0.1503 0.02186 0.01431 -0.1049 0.8284 0.0620
-5.500 -0.1254 0.02126 0.01366 -0.1045 0.8235 0.0659
-5.250 -0.0992 0.02055 0.01274 -0.1039 0.8200 0.0697
-5.000 -0.0754 0.01963 0.01181 -0.1034 0.8144 0.0742
-4.750 -0.0501 0.01917 0.01131 -0.1030 0.8091 0.0796
-4.500 -0.0241 0.01839 0.01044 -0.1025 0.8052 0.0853
-4.250 0.0014 0.01793 0.00999 -0.1021 0.8011 0.0926
-4.000 0.0253 0.01741 0.00948 -0.1016 0.7948 0.1005
-3.750 0.0519 0.01705 0.00905 -0.1012 0.7906 0.1112
-3.500 0.0781 0.01646 0.00849 -0.1008 0.7873 0.1252
-3.250 0.1015 0.01614 0.00827 -0.1004 0.7808 0.1432
-3.000 0.1267 0.01567 0.00792 -0.1000 0.7760 0.1702
-2.750 0.1528 0.01510 0.00753 -0.0998 0.7726 0.2151
-2.500 0.1757 0.01458 0.00740 -0.0994 0.7673 0.3005
-2.250 0.1960 0.01375 0.00734 -0.0985 0.7618 0.4838
-2.000 0.2168 0.01321 0.00740 -0.0966 0.7579 0.6592
-1.750 0.2401 0.01313 0.00748 -0.0949 0.7544 0.7406
-1.500 0.2605 0.01331 0.00774 -0.0930 0.7479 0.7877
-1.250 0.2833 0.01334 0.00776 -0.0913 0.7436 0.8232
-1.000 0.3070 0.01334 0.00769 -0.0895 0.7403 0.8525
-0.750 0.3255 0.01353 0.00791 -0.0873 0.7342 0.8771
-0.500 0.3466 0.01358 0.00791 -0.0853 0.7293 0.8996
-0.250 0.3724 0.01352 0.00778 -0.0840 0.7257 0.9197
0.000 0.4010 0.01359 0.00780 -0.0837 0.7210 0.9389
0.250 0.4379 0.01367 0.00783 -0.0853 0.7155 0.9558
0.500 0.4913 0.01361 0.00766 -0.0900 0.7116 0.9684
0.750 0.5616 0.01349 0.00738 -0.0981 0.7086 0.9814
1.000 0.6139 0.01353 0.00741 -0.1036 0.7023 0.9914
1.250 0.6592 0.01341 0.00723 -0.1074 0.6973 0.9985
1.500 0.6869 0.01333 0.00706 -0.1078 0.6934 1.0000
1.750 0.7023 0.01352 0.00727 -0.1061 0.6869 1.0000
2.000 0.7209 0.01357 0.00729 -0.1047 0.6816 1.0000
2.250 0.7430 0.01356 0.00720 -0.1038 0.6778 1.0000
2.500 0.7567 0.01379 0.00748 -0.1017 0.6712 1.0000
2.750 0.7755 0.01387 0.00752 -0.1002 0.6659 1.0000
3.000 0.7994 0.01388 0.00747 -0.0995 0.6622 1.0000
3.250 0.8145 0.01416 0.00779 -0.0976 0.6555 1.0000
3.500 0.8376 0.01425 0.00785 -0.0968 0.6501 1.0000
3.750 0.8663 0.01426 0.00777 -0.0969 0.6462 1.0000
4.000 0.8856 0.01455 0.00815 -0.0958 0.6390 1.0000
4.250 0.9127 0.01461 0.00818 -0.0957 0.6337 1.0000
4.500 0.9403 0.01472 0.00826 -0.0957 0.6287 1.0000
4.750 0.9629 0.01494 0.00855 -0.0951 0.6217 1.0000
5.000 0.9922 0.01497 0.00854 -0.0953 0.6167 1.0000
5.250 1.0159 0.01522 0.00885 -0.0948 0.6101 1.0000
5.500 1.0419 0.01536 0.00902 -0.0946 0.6039 1.0000
5.750 1.0720 0.01541 0.00903 -0.0950 0.5988 1.0000
6.000 1.0929 0.01564 0.00937 -0.0940 0.5903 1.0000
6.250 1.1238 0.01562 0.00930 -0.0945 0.5844 1.0000
6.500 1.1440 0.01590 0.00971 -0.0934 0.5760 1.0000
6.750 1.1733 0.01594 0.00972 -0.0937 0.5697 1.0000
7.000 1.1943 0.01619 0.01009 -0.0927 0.5612 1.0000
7.250 1.2236 0.01617 0.01002 -0.0928 0.5535 1.0000
7.500 1.2430 0.01618 0.01010 -0.0913 0.5405 1.0000
7.750 1.2625 0.01615 0.01009 -0.0898 0.5259 1.0000
8.000 1.2812 0.01624 0.01022 -0.0882 0.5119 1.0000
8.250 1.2998 0.01641 0.01043 -0.0867 0.4986 1.0000
8.500 1.3169 0.01661 0.01066 -0.0850 0.4845 1.0000
8.750 1.3326 0.01687 0.01095 -0.0830 0.4700 1.0000
9.000 1.3463 0.01719 0.01130 -0.0808 0.4548 1.0000
9.250 1.3562 0.01756 0.01170 -0.0779 0.4389 1.0000
9.500 1.3626 0.01806 0.01219 -0.0746 0.4220 1.0000
9.750 1.3674 0.01869 0.01281 -0.0713 0.4031 1.0000
10.000 1.3705 0.01950 0.01358 -0.0679 0.3822 1.0000
10.250 1.3708 0.02054 0.01457 -0.0645 0.3574 1.0000
10.500 1.3685 0.02184 0.01580 -0.0611 0.3295 1.0000
10.750 1.3622 0.02354 0.01735 -0.0576 0.2974 1.0000
11.000 1.3523 0.02565 0.01928 -0.0541 0.2635 1.0000
11.250 1.3402 0.02816 0.02158 -0.0509 0.2258 1.0000
11.500 1.3246 0.03115 0.02433 -0.0479 0.1883 1.0000
11.750 1.3095 0.03437 0.02732 -0.0453 0.1516 1.0000
12.000 1.2941 0.03786 0.03058 -0.0431 0.1212 1.0000
12.250 1.2837 0.04115 0.03373 -0.0414 0.1007 1.0000
12.500 1.2756 0.04439 0.03690 -0.0401 0.0876 1.0000
12.750 1.2705 0.04749 0.03998 -0.0390 0.0788 1.0000
13.000 1.2648 0.05073 0.04319 -0.0382 0.0723 1.0000
13.250 1.2660 0.05337 0.04591 -0.0375 0.0668 1.0000
13.500 1.2649 0.05629 0.04883 -0.0370 0.0625 1.0000
13.750 1.2654 0.05907 0.05164 -0.0364 0.0590 1.0000
14.000 1.2700 0.06149 0.05414 -0.0361 0.0555 1.0000
14.250 1.2728 0.06410 0.05674 -0.0357 0.0526 1.0000
14.500 1.2779 0.06637 0.05901 -0.0351 0.0500 1.0000
14.750 1.2852 0.06855 0.06131 -0.0348 0.0477 1.0000
15.000 1.2924 0.07074 0.06356 -0.0345 0.0455 1.0000
15.250 1.3003 0.07276 0.06555 -0.0342 0.0434 1.0000
15.500 1.3122 0.07433 0.06717 -0.0334 0.0414 1.0000
15.750 1.3208 0.07647 0.06944 -0.0332 0.0399 1.0000
16.000 1.3299 0.07854 0.07162 -0.0330 0.0384 1.0000
16.250 1.3387 0.08064 0.07376 -0.0329 0.0369 1.0000
16.500 1.3615 0.08113 0.07416 -0.0315 0.0349 1.0000
16.750 1.3613 0.08445 0.07771 -0.0320 0.0341 1.0000
17.000 1.3642 0.08750 0.08098 -0.0323 0.0333 1.0000
17.250 1.3672 0.09058 0.08425 -0.0326 0.0323 1.0000
17.500 1.3708 0.09362 0.08743 -0.0330 0.0315 1.0000
17.750 1.3726 0.09688 0.09085 -0.0336 0.0308 1.0000
18.000 1.3752 0.10005 0.09413 -0.0342 0.0301 1.0000
18.250 1.3814 0.10276 0.09689 -0.0346 0.0293 1.0000
18.500 1.3845 0.10637 0.10064 -0.0349 0.0286 1.0000
18.750 1.3705 0.11194 0.10649 -0.0372 0.0283 1.0000
19.000 1.3565 0.11777 0.11259 -0.0397 0.0281 1.0000
19.250 1.3413 0.12406 0.11913 -0.0427 0.0279 1.0000
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