FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-140 (fx84w140-il) Reynolds number: 200,000 Max Cl/Cd: 79.68 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w140-il-200000-n5.txt Download as CSV file: xf-fx84w140-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2563 0.08836 0.08452 -0.0815 0.9134 0.0230
-10.750 -0.2684 0.08148 0.07764 -0.0852 0.9034 0.0231
-10.500 -0.4320 0.04574 0.04159 -0.1097 0.8818 0.0219
-10.250 -0.4720 0.04076 0.03625 -0.1089 0.8683 0.0218
-10.000 -0.4884 0.03712 0.03223 -0.1073 0.8589 0.0220
-9.750 -0.4929 0.03404 0.02872 -0.1058 0.8520 0.0225
-9.500 -0.4896 0.03127 0.02552 -0.1045 0.8451 0.0230
-9.250 -0.4810 0.02881 0.02258 -0.1032 0.8389 0.0238
-9.000 -0.4658 0.02726 0.02075 -0.1022 0.8341 0.0245
-8.750 -0.4454 0.02651 0.01994 -0.1018 0.8281 0.0253
-8.500 -0.4252 0.02564 0.01892 -0.1012 0.8229 0.0263
-8.000 -0.3841 0.02325 0.01598 -0.0999 0.8130 0.0286
-7.750 -0.3623 0.02217 0.01473 -0.0994 0.8079 0.0296
-7.500 -0.3391 0.02148 0.01395 -0.0990 0.8038 0.0307
-7.250 -0.3152 0.02088 0.01325 -0.0987 0.7987 0.0323
-7.000 -0.2909 0.02017 0.01235 -0.0983 0.7937 0.0343
-6.750 -0.2670 0.01941 0.01149 -0.0979 0.7893 0.0358
-6.500 -0.2423 0.01885 0.01086 -0.0976 0.7852 0.0375
-6.250 -0.2172 0.01833 0.01027 -0.0973 0.7800 0.0397
-6.000 -0.1920 0.01779 0.00959 -0.0970 0.7754 0.0422
-5.750 -0.1668 0.01730 0.00906 -0.0967 0.7716 0.0447
-5.500 -0.1413 0.01688 0.00859 -0.0965 0.7665 0.0477
-5.250 -0.1157 0.01644 0.00807 -0.0962 0.7617 0.0510
-5.000 -0.0899 0.01604 0.00764 -0.0960 0.7577 0.0546
-4.750 -0.0636 0.01571 0.00721 -0.0958 0.7535 0.0588
-4.500 -0.0380 0.01532 0.00685 -0.0957 0.7483 0.0637
-4.250 -0.0116 0.01502 0.00649 -0.0955 0.7438 0.0693
-4.000 0.0148 0.01468 0.00612 -0.0953 0.7401 0.0762
-3.750 0.0412 0.01444 0.00585 -0.0952 0.7349 0.0843
-3.500 0.0677 0.01417 0.00559 -0.0951 0.7299 0.0946
-3.250 0.0945 0.01390 0.00532 -0.0950 0.7258 0.1077
-3.000 0.1212 0.01367 0.00511 -0.0949 0.7213 0.1243
-2.750 0.1476 0.01344 0.00495 -0.0949 0.7161 0.1458
-2.500 0.1743 0.01319 0.00476 -0.0948 0.7116 0.1755
-2.250 0.2011 0.01291 0.00457 -0.0948 0.7079 0.2157
-1.750 0.2522 0.01220 0.00438 -0.0946 0.6978 0.3601
-1.500 0.2767 0.01169 0.00429 -0.0942 0.6938 0.4873
-1.250 0.3000 0.01135 0.00438 -0.0933 0.6891 0.6083
-1.000 0.3241 0.01123 0.00447 -0.0923 0.6841 0.6858
-0.750 0.3492 0.01119 0.00451 -0.0915 0.6797 0.7355
-0.500 0.3745 0.01120 0.00453 -0.0906 0.6755 0.7716
-0.250 0.3992 0.01124 0.00461 -0.0898 0.6702 0.8004
0.000 0.4239 0.01127 0.00464 -0.0889 0.6655 0.8244
0.250 0.4491 0.01130 0.00462 -0.0880 0.6617 0.8469
0.500 0.4722 0.01136 0.00471 -0.0869 0.6561 0.8686
0.750 0.4939 0.01140 0.00477 -0.0852 0.6512 0.8964
1.000 0.5184 0.01141 0.00475 -0.0839 0.6470 0.9208
1.250 0.5466 0.01146 0.00478 -0.0839 0.6417 0.9356
1.500 0.5770 0.01150 0.00480 -0.0845 0.6364 0.9466
1.750 0.6098 0.01153 0.00477 -0.0856 0.6319 0.9567
2.000 0.6447 0.01160 0.00481 -0.0873 0.6265 0.9652
2.250 0.6794 0.01166 0.00486 -0.0889 0.6210 0.9741
2.500 0.7152 0.01172 0.00487 -0.0908 0.6164 0.9826
2.750 0.7517 0.01181 0.00495 -0.0929 0.6110 0.9910
3.000 0.7849 0.01190 0.00504 -0.0944 0.6053 1.0000
3.250 0.8064 0.01201 0.00510 -0.0934 0.6007 1.0000
3.500 0.8283 0.01215 0.00524 -0.0925 0.5952 1.0000
3.750 0.8518 0.01229 0.00538 -0.0919 0.5895 1.0000
4.000 0.8773 0.01241 0.00546 -0.0917 0.5846 1.0000
4.250 0.9013 0.01258 0.00567 -0.0912 0.5783 1.0000
4.500 0.9265 0.01273 0.00581 -0.0909 0.5723 1.0000
4.750 0.9521 0.01288 0.00597 -0.0907 0.5666 1.0000
5.000 0.9765 0.01306 0.00619 -0.0903 0.5599 1.0000
5.250 1.0024 0.01322 0.00632 -0.0901 0.5541 1.0000
5.500 1.0266 0.01342 0.00659 -0.0897 0.5475 1.0000
5.750 1.0515 0.01361 0.00680 -0.0894 0.5411 1.0000
6.000 1.0759 0.01381 0.00702 -0.0889 0.5341 1.0000
6.250 1.0995 0.01401 0.00725 -0.0884 0.5256 1.0000
6.500 1.1229 0.01423 0.00751 -0.0878 0.5176 1.0000
6.750 1.1463 0.01445 0.00777 -0.0872 0.5098 1.0000
7.000 1.1689 0.01470 0.00807 -0.0865 0.5017 1.0000
7.250 1.1912 0.01495 0.00835 -0.0857 0.4929 1.0000
7.500 1.2101 0.01522 0.00865 -0.0844 0.4797 1.0000
7.750 1.2256 0.01554 0.00892 -0.0824 0.4613 1.0000
8.000 1.2384 0.01594 0.00929 -0.0801 0.4404 1.0000
8.250 1.2490 0.01638 0.00970 -0.0774 0.4213 1.0000
8.500 1.2580 0.01691 0.01019 -0.0746 0.4027 1.0000
8.750 1.2655 0.01757 0.01079 -0.0717 0.3820 1.0000
9.000 1.2718 0.01835 0.01151 -0.0688 0.3595 1.0000
9.250 1.2762 0.01930 0.01238 -0.0659 0.3362 1.0000
9.500 1.2787 0.02044 0.01343 -0.0630 0.3102 1.0000
9.750 1.2796 0.02177 0.01465 -0.0602 0.2831 1.0000
10.000 1.2784 0.02335 0.01611 -0.0574 0.2549 1.0000
10.250 1.2760 0.02513 0.01775 -0.0547 0.2260 1.0000
10.500 1.2732 0.02707 0.01956 -0.0522 0.1989 1.0000
10.750 1.2700 0.02917 0.02152 -0.0500 0.1719 1.0000
11.000 1.2665 0.03140 0.02363 -0.0479 0.1454 1.0000
11.250 1.2637 0.03370 0.02580 -0.0461 0.1220 1.0000
11.500 1.2618 0.03601 0.02803 -0.0445 0.1017 1.0000
11.750 1.2619 0.03826 0.03024 -0.0432 0.0873 1.0000
12.000 1.2627 0.04055 0.03250 -0.0421 0.0755 1.0000
12.250 1.2647 0.04279 0.03474 -0.0411 0.0667 1.0000
12.500 1.2664 0.04515 0.03711 -0.0403 0.0598 1.0000
12.750 1.2698 0.04741 0.03942 -0.0396 0.0542 1.0000
13.000 1.2717 0.04990 0.04194 -0.0390 0.0498 1.0000
13.250 1.2756 0.05224 0.04436 -0.0386 0.0462 1.0000
13.500 1.2769 0.05493 0.04708 -0.0382 0.0431 1.0000
13.750 1.2794 0.05755 0.04979 -0.0379 0.0407 1.0000
14.000 1.2828 0.06012 0.05245 -0.0378 0.0384 1.0000
14.250 1.2846 0.06293 0.05532 -0.0377 0.0365 1.0000
14.500 1.2835 0.06617 0.05860 -0.0377 0.0348 1.0000
14.750 1.2874 0.06885 0.06140 -0.0378 0.0332 1.0000
15.000 1.2902 0.07170 0.06437 -0.0380 0.0318 1.0000
15.250 1.2920 0.07472 0.06748 -0.0382 0.0305 1.0000
15.500 1.2923 0.07802 0.07084 -0.0387 0.0294 1.0000
15.750 1.2915 0.08147 0.07435 -0.0391 0.0285 1.0000
16.000 1.2948 0.08443 0.07743 -0.0396 0.0275 1.0000
16.250 1.2974 0.08752 0.08063 -0.0401 0.0264 1.0000
16.500 1.2994 0.09073 0.08394 -0.0408 0.0254 1.0000
16.750 1.3010 0.09404 0.08734 -0.0415 0.0246 1.0000
17.000 1.3015 0.09752 0.09089 -0.0424 0.0239 1.0000
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