FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-175 (fx84w175-il) Reynolds number: 50,000 Max Cl/Cd: 10.29 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w175-il-50000-n5.txt Download as CSV file: xf-fx84w175-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-175
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2405 0.11867 0.11142 -0.0807 0.9610 0.0792
-11.500 -0.2366 0.11320 0.10593 -0.0855 0.9573 0.0795
-11.250 -0.2414 0.10761 0.10035 -0.0895 0.9511 0.0800
-11.000 -0.2313 0.10366 0.09640 -0.0925 0.9464 0.0811
-10.750 -0.2270 0.09803 0.09074 -0.0974 0.9428 0.0814
-10.500 -0.2441 0.09101 0.08374 -0.1018 0.9352 0.0809
-10.250 -0.2906 0.07784 0.07045 -0.1129 0.9282 0.0800
-10.000 -0.3217 0.07254 0.06507 -0.1152 0.9178 0.0797
-9.750 -0.3548 0.06780 0.06014 -0.1166 0.9087 0.0797
-9.500 -0.3858 0.06506 0.05725 -0.1138 0.8978 0.0797
-9.250 -0.4128 0.06229 0.05423 -0.1108 0.8882 0.0799
-9.000 -0.4147 0.06019 0.05201 -0.1094 0.8811 0.0812
-8.750 -0.3978 0.05842 0.05017 -0.1100 0.8771 0.0835
-8.500 -0.4150 0.05719 0.04880 -0.1052 0.8669 0.0843
-8.250 -0.4113 0.05463 0.04591 -0.1044 0.8616 0.0862
-8.000 -0.4193 0.05286 0.04385 -0.1008 0.8537 0.0875
-7.750 -0.4191 0.05062 0.04118 -0.0985 0.8470 0.0895
-7.500 -0.4011 0.04858 0.03882 -0.0985 0.8431 0.0926
-7.250 -0.3996 0.04795 0.03813 -0.0952 0.8355 0.0947
-7.000 -0.3867 0.04670 0.03668 -0.0937 0.8297 0.0978
-6.750 -0.3644 0.04488 0.03438 -0.0938 0.8260 0.1023
-6.500 -0.3536 0.04409 0.03351 -0.0917 0.8200 0.1056
-6.250 -0.3431 0.04347 0.03283 -0.0895 0.8133 0.1092
-6.000 -0.3178 0.04228 0.03130 -0.0896 0.8094 0.1153
-5.750 -0.2862 0.04129 0.03027 -0.0906 0.8067 0.1217
-5.500 -0.2887 0.04116 0.03008 -0.0862 0.7980 0.1254
-5.250 -0.2657 0.04043 0.02917 -0.0857 0.7934 0.1330
-5.000 -0.2353 0.03971 0.02840 -0.0864 0.7902 0.1424
-4.750 -0.2256 0.03948 0.02811 -0.0838 0.7838 0.1495
-4.500 -0.2104 0.03920 0.02780 -0.0822 0.7778 0.1587
-4.250 -0.1833 0.03866 0.02725 -0.0822 0.7740 0.1716
-4.000 -0.1511 0.03804 0.02661 -0.0830 0.7714 0.1886
-3.750 -0.1539 0.03831 0.02685 -0.0788 0.7626 0.1984
-3.500 -0.1313 0.03791 0.02652 -0.0783 0.7581 0.2180
-3.250 -0.1023 0.03735 0.02604 -0.0787 0.7550 0.2469
-3.000 -0.0960 0.03743 0.02623 -0.0761 0.7480 0.2708
-2.750 -0.0805 0.03718 0.02619 -0.0748 0.7425 0.3085
-2.500 -0.0568 0.03658 0.02598 -0.0743 0.7388 0.3756
-2.250 -0.0315 0.03597 0.02596 -0.0734 0.7362 0.4832
-2.000 -0.0380 0.03666 0.02697 -0.0684 0.7270 0.5488
-1.750 -0.0207 0.03686 0.02741 -0.0654 0.7228 0.6399
-1.500 0.0021 0.03706 0.02765 -0.0630 0.7198 0.7092
-1.250 -0.0002 0.03794 0.02853 -0.0585 0.7115 0.7480
-1.000 0.0152 0.03835 0.02891 -0.0555 0.7067 0.7909
-0.750 0.0384 0.03859 0.02905 -0.0534 0.7034 0.8313
-0.500 0.0450 0.03934 0.02976 -0.0501 0.6965 0.8645
-0.250 0.0690 0.03988 0.03022 -0.0493 0.6911 0.8997
0.000 0.1208 0.04038 0.03055 -0.0531 0.6880 0.9350
0.250 0.2029 0.04096 0.03089 -0.0626 0.6861 0.9661
0.750 0.2817 0.04257 0.03223 -0.0708 0.6738 1.0000
1.000 0.2928 0.04251 0.03204 -0.0687 0.6698 1.0000
1.250 0.2707 0.04324 0.03272 -0.0627 0.6611 1.0000
1.500 0.2778 0.04354 0.03288 -0.0604 0.6555 1.0000
1.750 0.3008 0.04363 0.03282 -0.0599 0.6522 1.0000
2.000 0.2941 0.04484 0.03395 -0.0567 0.6434 1.0000
2.250 0.3139 0.04533 0.03431 -0.0563 0.6384 1.0000
2.500 0.3425 0.04556 0.03442 -0.0566 0.6353 1.0000
2.750 0.3418 0.04702 0.03581 -0.0545 0.6265 1.0000
3.000 0.3634 0.04764 0.03633 -0.0543 0.6217 1.0000
3.250 0.3931 0.04792 0.03651 -0.0548 0.6185 1.0000
3.500 0.3935 0.04956 0.03811 -0.0530 0.6097 1.0000
3.750 0.4155 0.05025 0.03872 -0.0529 0.6048 1.0000
4.000 0.4457 0.05054 0.03894 -0.0534 0.6017 1.0000
4.250 0.4451 0.05239 0.04077 -0.0517 0.5925 1.0000
4.500 0.4678 0.05309 0.04142 -0.0517 0.5878 1.0000
4.750 0.4981 0.05340 0.04168 -0.0521 0.5847 1.0000
5.000 0.4956 0.05549 0.04377 -0.0505 0.5750 1.0000
5.250 0.5198 0.05614 0.04439 -0.0505 0.5706 1.0000
5.500 0.5505 0.05642 0.04464 -0.0510 0.5677 1.0000
5.750 0.5454 0.05880 0.04704 -0.0493 0.5572 1.0000
6.000 0.5713 0.05937 0.04760 -0.0495 0.5532 1.0000
6.250 0.6028 0.05957 0.04779 -0.0499 0.5505 1.0000
6.500 0.5945 0.06229 0.05053 -0.0483 0.5392 1.0000
6.750 0.6224 0.06271 0.05097 -0.0485 0.5356 1.0000
7.000 0.6225 0.06502 0.05331 -0.0474 0.5264 1.0000
7.250 0.6440 0.06585 0.05416 -0.0473 0.5211 1.0000
7.500 0.6742 0.06606 0.05440 -0.0475 0.5179 1.0000
7.750 0.6678 0.06892 0.05731 -0.0464 0.5069 1.0000
8.000 0.6949 0.06931 0.05773 -0.0464 0.5028 1.0000
8.500 0.7166 0.07259 0.06112 -0.0455 0.4879 1.0000
8.750 0.7475 0.07261 0.06120 -0.0456 0.4847 1.0000
9.000 0.7393 0.07588 0.06453 -0.0447 0.4730 1.0000
9.250 0.7679 0.07602 0.06472 -0.0446 0.4691 1.0000
9.500 0.7631 0.07912 0.06790 -0.0440 0.4582 1.0000
9.750 0.7890 0.07943 0.06829 -0.0439 0.4535 1.0000
10.000 0.7879 0.08228 0.07122 -0.0434 0.4433 1.0000
10.250 0.8104 0.08288 0.07190 -0.0432 0.4378 1.0000
10.750 0.8319 0.08636 0.07556 -0.0427 0.4220 1.0000
11.000 0.8642 0.08585 0.07514 -0.0424 0.4188 1.0000
11.250 0.8537 0.08983 0.07921 -0.0422 0.4060 1.0000
11.500 0.8853 0.08926 0.07876 -0.0418 0.4026 1.0000
11.750 0.8756 0.09328 0.08286 -0.0417 0.3898 1.0000
12.000 0.9070 0.09260 0.08229 -0.0413 0.3863 1.0000
12.250 0.8976 0.09670 0.08649 -0.0414 0.3734 1.0000
12.500 0.9288 0.09586 0.08577 -0.0408 0.3697 1.0000
12.750 0.9201 0.10001 0.09003 -0.0411 0.3569 1.0000
13.250 0.9436 0.10306 0.09330 -0.0407 0.3401 1.0000
13.750 0.9696 0.10549 0.09598 -0.0402 0.3232 1.0000
14.250 0.9992 0.10709 0.09781 -0.0395 0.3064 1.0000
14.750 0.9911 0.11477 0.10569 -0.0409 0.2813 1.0000
15.250 1.0189 0.11638 0.10755 -0.0403 0.2629 1.0000
15.500 1.0613 0.11195 0.10327 -0.0381 0.2588 1.0000
15.750 1.0546 0.11631 0.10773 -0.0392 0.2453 1.0000
16.000 1.0526 0.11998 0.11150 -0.0402 0.2328 1.0000
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