FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-140 (fx84w140-il) Reynolds number: 500,000 Max Cl/Cd: 118.11 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w140-il-500000.txt Download as CSV file: xf-fx84w140-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1834 0.10524 0.10275 -0.0647 0.8788 0.0298
-11.750 -0.4783 0.04892 0.04617 -0.1075 0.9228 0.0197
-11.500 -0.5104 0.04257 0.03958 -0.1117 0.9050 0.0194
-11.250 -0.5407 0.03835 0.03509 -0.1120 0.8903 0.0194
-11.000 -0.5667 0.03546 0.03191 -0.1091 0.8784 0.0195
-10.750 -0.5809 0.03267 0.02878 -0.1065 0.8692 0.0196
-10.500 -0.5828 0.03020 0.02594 -0.1046 0.8618 0.0198
-10.250 -0.5795 0.02777 0.02315 -0.1029 0.8550 0.0200
-10.000 -0.5713 0.02540 0.02053 -0.1016 0.8495 0.0205
-9.750 -0.5530 0.02434 0.01939 -0.1010 0.8437 0.0210
-9.500 -0.5332 0.02349 0.01841 -0.1004 0.8385 0.0215
-9.250 -0.5133 0.02255 0.01729 -0.0997 0.8338 0.0221
-9.000 -0.4925 0.02151 0.01609 -0.0991 0.8283 0.0229
-8.750 -0.4706 0.02063 0.01499 -0.0986 0.8234 0.0237
-8.500 -0.4494 0.01951 0.01361 -0.0979 0.8191 0.0244
-8.250 -0.4266 0.01856 0.01264 -0.0976 0.8140 0.0254
-8.000 -0.4021 0.01800 0.01202 -0.0974 0.8091 0.0264
-7.750 -0.3775 0.01738 0.01128 -0.0970 0.8049 0.0274
-7.500 -0.3524 0.01679 0.01054 -0.0967 0.8005 0.0285
-7.250 -0.3281 0.01591 0.00954 -0.0964 0.7955 0.0297
-7.000 -0.3029 0.01536 0.00897 -0.0962 0.7910 0.0312
-6.750 -0.2767 0.01503 0.00856 -0.0960 0.7870 0.0329
-6.500 -0.2501 0.01464 0.00809 -0.0959 0.7823 0.0344
-6.250 -0.2254 0.01386 0.00727 -0.0956 0.7776 0.0364
-6.000 -0.1990 0.01352 0.00689 -0.0955 0.7734 0.0384
-5.750 -0.1718 0.01328 0.00657 -0.0954 0.7691 0.0409
-5.500 -0.1460 0.01273 0.00600 -0.0953 0.7643 0.0436
-5.250 -0.1191 0.01242 0.00567 -0.0952 0.7598 0.0464
-5.000 -0.0918 0.01222 0.00538 -0.0951 0.7557 0.0493
-4.750 -0.0655 0.01176 0.00494 -0.0950 0.7509 0.0534
-4.500 -0.0380 0.01154 0.00470 -0.0951 0.7460 0.0576
-4.250 -0.0110 0.01122 0.00433 -0.0950 0.7417 0.0627
-4.000 0.0166 0.01102 0.00412 -0.0950 0.7374 0.0687
-3.750 0.0438 0.01073 0.00385 -0.0950 0.7325 0.0765
-3.500 0.0715 0.01052 0.00362 -0.0951 0.7281 0.0860
-3.250 0.0992 0.01034 0.00341 -0.0951 0.7241 0.0986
-3.000 0.1267 0.01009 0.00326 -0.0952 0.7193 0.1166
-2.750 0.1543 0.00986 0.00311 -0.0953 0.7145 0.1405
-2.500 0.1819 0.00964 0.00296 -0.0954 0.7104 0.1738
-2.250 0.2093 0.00939 0.00286 -0.0955 0.7061 0.2217
-2.000 0.2363 0.00904 0.00277 -0.0957 0.7011 0.2918
-1.750 0.2625 0.00857 0.00266 -0.0958 0.6966 0.4065
-1.500 0.2881 0.00809 0.00262 -0.0956 0.6926 0.5555
-1.250 0.3140 0.00780 0.00267 -0.0953 0.6877 0.6556
-1.000 0.3407 0.00770 0.00270 -0.0950 0.6829 0.7148
-0.750 0.3678 0.00768 0.00272 -0.0947 0.6786 0.7535
-0.500 0.3949 0.00769 0.00277 -0.0944 0.6740 0.7827
-0.250 0.4218 0.00769 0.00281 -0.0941 0.6688 0.8051
0.000 0.4487 0.00772 0.00283 -0.0938 0.6642 0.8244
0.250 0.4755 0.00777 0.00287 -0.0934 0.6596 0.8416
0.500 0.5019 0.00779 0.00291 -0.0930 0.6543 0.8570
0.750 0.5280 0.00782 0.00294 -0.0925 0.6495 0.8715
1.000 0.5538 0.00789 0.00298 -0.0919 0.6451 0.8859
1.250 0.5786 0.00792 0.00304 -0.0911 0.6401 0.9003
1.500 0.6003 0.00794 0.00308 -0.0895 0.6352 0.9187
1.750 0.6207 0.00800 0.00311 -0.0876 0.6307 0.9379
2.000 0.6443 0.00799 0.00314 -0.0866 0.6256 0.9517
2.250 0.6724 0.00801 0.00316 -0.0866 0.6206 0.9621
2.500 0.7036 0.00808 0.00317 -0.0874 0.6159 0.9717
2.750 0.7398 0.00813 0.00323 -0.0893 0.6105 0.9783
3.000 0.7765 0.00818 0.00327 -0.0914 0.6049 0.9848
3.500 0.8529 0.00833 0.00339 -0.0962 0.5935 0.9947
3.750 0.8910 0.00840 0.00345 -0.0987 0.5875 1.0000
4.000 0.9097 0.00851 0.00353 -0.0972 0.5823 1.0000
4.250 0.9310 0.00859 0.00363 -0.0962 0.5762 1.0000
4.500 0.9559 0.00872 0.00372 -0.0958 0.5707 1.0000
4.750 0.9818 0.00884 0.00386 -0.0957 0.5648 1.0000
5.000 1.0077 0.00894 0.00397 -0.0955 0.5576 1.0000
5.250 1.0338 0.00909 0.00409 -0.0954 0.5508 1.0000
5.500 1.0598 0.00921 0.00424 -0.0953 0.5436 1.0000
5.750 1.0859 0.00939 0.00438 -0.0952 0.5372 1.0000
6.000 1.1116 0.00951 0.00456 -0.0950 0.5298 1.0000
6.250 1.1369 0.00971 0.00472 -0.0947 0.5225 1.0000
6.500 1.1610 0.00983 0.00489 -0.0943 0.5114 1.0000
6.750 1.1834 0.01002 0.00505 -0.0935 0.4965 1.0000
7.000 1.2053 0.01024 0.00525 -0.0926 0.4811 1.0000
7.250 1.2269 0.01048 0.00548 -0.0917 0.4669 1.0000
7.500 1.2482 0.01075 0.00573 -0.0908 0.4537 1.0000
7.750 1.2686 0.01104 0.00601 -0.0897 0.4405 1.0000
8.000 1.2874 0.01138 0.00633 -0.0883 0.4253 1.0000
8.250 1.3043 0.01175 0.00667 -0.0867 0.4084 1.0000
8.500 1.3167 0.01218 0.00705 -0.0842 0.3902 1.0000
8.750 1.3252 0.01274 0.00754 -0.0812 0.3702 1.0000
9.000 1.3330 0.01340 0.00814 -0.0782 0.3464 1.0000
9.250 1.3378 0.01426 0.00889 -0.0750 0.3199 1.0000
9.500 1.3400 0.01533 0.00981 -0.0717 0.2896 1.0000
9.750 1.3399 0.01663 0.01095 -0.0683 0.2575 1.0000
10.000 1.3383 0.01813 0.01227 -0.0650 0.2240 1.0000
10.250 1.3346 0.01986 0.01381 -0.0617 0.1913 1.0000
10.500 1.3318 0.02167 0.01544 -0.0588 0.1587 1.0000
10.750 1.3278 0.02367 0.01726 -0.0560 0.1271 1.0000
11.000 1.3242 0.02575 0.01919 -0.0535 0.1003 1.0000
11.250 1.3226 0.02778 0.02111 -0.0514 0.0810 1.0000
11.500 1.3237 0.02971 0.02298 -0.0496 0.0672 1.0000
11.750 1.3259 0.03162 0.02486 -0.0480 0.0575 1.0000
12.000 1.3278 0.03364 0.02686 -0.0466 0.0502 1.0000
12.250 1.3329 0.03545 0.02869 -0.0455 0.0457 1.0000
12.500 1.3342 0.03768 0.03095 -0.0442 0.0418 1.0000
12.750 1.3411 0.03946 0.03279 -0.0434 0.0391 1.0000
13.000 1.3445 0.04162 0.03498 -0.0425 0.0367 1.0000
13.250 1.3451 0.04413 0.03753 -0.0417 0.0345 1.0000
13.500 1.3519 0.04607 0.03956 -0.0411 0.0330 1.0000
13.750 1.3569 0.04827 0.04182 -0.0406 0.0315 1.0000
14.000 1.3586 0.05084 0.04443 -0.0402 0.0301 1.0000
14.250 1.3542 0.05416 0.04781 -0.0397 0.0287 1.0000
14.500 1.3606 0.05637 0.05012 -0.0395 0.0278 1.0000
14.750 1.3654 0.05879 0.05262 -0.0393 0.0267 1.0000
15.000 1.3694 0.06134 0.05524 -0.0393 0.0257 1.0000
15.250 1.3718 0.06414 0.05809 -0.0393 0.0248 1.0000
15.500 1.3691 0.06761 0.06161 -0.0394 0.0239 1.0000
15.750 1.3659 0.07119 0.06526 -0.0396 0.0233 1.0000
16.000 1.3708 0.07384 0.06802 -0.0398 0.0227 1.0000
16.250 1.3746 0.07667 0.07094 -0.0402 0.0219 1.0000
16.500 1.3770 0.07972 0.07407 -0.0406 0.0212 1.0000
16.750 1.3800 0.08274 0.07715 -0.0412 0.0206 1.0000
17.000 1.3812 0.08602 0.08049 -0.0418 0.0201 1.0000
17.250 1.3789 0.08972 0.08423 -0.0425 0.0194 1.0000
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