WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.02 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx08s176-il-1000000.txt Download as CSV file: xf-fx08s176-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 08-S-176 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0586 0.08835 0.08473 -0.0959 0.5728 0.0131
-10.250 -0.0657 0.08179 0.07822 -0.0996 0.5723 0.0142
-10.000 -0.0656 0.07792 0.07436 -0.1014 0.5716 0.0142
-9.750 -0.0695 0.07321 0.06967 -0.1039 0.5709 0.0142
-9.500 -0.0783 0.06739 0.06389 -0.1076 0.5701 0.0143
-9.250 -0.3732 0.02749 0.02290 -0.0980 0.5723 0.0101
-9.000 -0.3698 0.02469 0.01970 -0.0952 0.5714 0.0105
-8.750 -0.3526 0.02370 0.01851 -0.0940 0.5703 0.0107
-8.500 -0.3487 0.02047 0.01484 -0.0913 0.5693 0.0113
-8.250 -0.3268 0.01988 0.01419 -0.0907 0.5688 0.0115
-8.000 -0.3028 0.01962 0.01391 -0.0903 0.5682 0.0119
-7.750 -0.2790 0.01927 0.01350 -0.0899 0.5676 0.0123
-7.500 -0.2551 0.01880 0.01295 -0.0895 0.5669 0.0128
-7.250 -0.2315 0.01816 0.01220 -0.0890 0.5661 0.0134
-7.000 -0.2064 0.01780 0.01174 -0.0887 0.5652 0.0139
-6.750 -0.1803 0.01774 0.01160 -0.0885 0.5642 0.0143
-6.500 -0.1598 0.01581 0.00949 -0.0877 0.5633 0.0152
-6.250 -0.1342 0.01549 0.00915 -0.0876 0.5624 0.0158
-6.000 -0.1082 0.01516 0.00876 -0.0874 0.5615 0.0165
-5.750 -0.0822 0.01474 0.00829 -0.0873 0.5606 0.0172
-5.500 -0.0559 0.01439 0.00787 -0.0871 0.5598 0.0179
-5.250 -0.0288 0.01427 0.00770 -0.0872 0.5590 0.0185
-5.000 -0.0041 0.01351 0.00684 -0.0868 0.5582 0.0193
-4.750 0.0201 0.01285 0.00614 -0.0863 0.5573 0.0202
-4.500 0.0460 0.01256 0.00582 -0.0862 0.5563 0.0210
-4.250 0.0724 0.01241 0.00564 -0.0861 0.5549 0.0219
-4.000 0.0990 0.01219 0.00540 -0.0861 0.5542 0.0229
-3.750 0.1255 0.01191 0.00510 -0.0860 0.5536 0.0237
-3.500 0.1522 0.01168 0.00486 -0.0859 0.5529 0.0243
-3.250 0.1787 0.01141 0.00455 -0.0859 0.5521 0.0249
-3.000 0.2047 0.01106 0.00417 -0.0857 0.5513 0.0268
-2.750 0.2320 0.01089 0.00399 -0.0858 0.5505 0.0287
-2.500 0.2597 0.01075 0.00384 -0.0860 0.5496 0.0304
-2.250 0.2875 0.01063 0.00370 -0.0861 0.5486 0.0321
-2.000 0.3152 0.01045 0.00355 -0.0863 0.5477 0.0405
-1.750 0.3430 0.01029 0.00348 -0.0865 0.5466 0.0651
-1.500 0.3711 0.01017 0.00339 -0.0868 0.5456 0.0802
-1.250 0.3990 0.01000 0.00331 -0.0871 0.5447 0.1109
-1.000 0.4249 0.00941 0.00320 -0.0875 0.5435 0.2807
-0.750 0.4503 0.00809 0.00304 -0.0884 0.5422 0.6592
-0.500 0.4767 0.00797 0.00333 -0.0882 0.5403 0.7925
-0.250 0.5046 0.00807 0.00347 -0.0882 0.5394 0.8217
0.000 0.5322 0.00821 0.00362 -0.0881 0.5385 0.8373
0.250 0.5606 0.00833 0.00372 -0.0882 0.5373 0.8468
0.500 0.5870 0.00842 0.00383 -0.0879 0.5359 0.8521
0.750 0.6148 0.00852 0.00391 -0.0879 0.5343 0.8585
1.000 0.6424 0.00858 0.00395 -0.0880 0.5329 0.8630
1.250 0.6679 0.00869 0.00406 -0.0874 0.5316 0.8676
1.500 0.6954 0.00878 0.00413 -0.0874 0.5304 0.8720
1.750 0.7249 0.00883 0.00416 -0.0881 0.5293 0.8745
2.000 0.7542 0.00889 0.00418 -0.0887 0.5281 0.8763
2.250 0.7799 0.00900 0.00428 -0.0883 0.5267 0.8791
2.500 0.8062 0.00911 0.00440 -0.0882 0.5255 0.8819
2.750 0.8343 0.00913 0.00444 -0.0885 0.5245 0.8836
3.000 0.8629 0.00915 0.00447 -0.0890 0.5234 0.8852
3.250 0.8916 0.00917 0.00451 -0.0895 0.5220 0.8871
3.500 0.9208 0.00921 0.00455 -0.0901 0.5206 0.8887
3.750 0.9503 0.00923 0.00458 -0.0909 0.5192 0.8899
4.000 0.9787 0.00922 0.00457 -0.0913 0.5176 0.8913
4.250 1.0060 0.00920 0.00456 -0.0915 0.5161 0.8926
4.500 1.0337 0.00922 0.00458 -0.0918 0.5145 0.8938
4.750 1.0616 0.00930 0.00465 -0.0922 0.5126 0.8949
5.000 1.0891 0.00934 0.00473 -0.0925 0.5110 0.8961
5.250 1.1167 0.00936 0.00480 -0.0929 0.5095 0.8975
5.500 1.1445 0.00938 0.00486 -0.0933 0.5076 0.8989
5.750 1.1726 0.00939 0.00490 -0.0937 0.5053 0.9003
6.000 1.2006 0.00934 0.00487 -0.0942 0.5019 0.9014
6.250 1.2281 0.00935 0.00486 -0.0946 0.4973 0.9025
6.500 1.2561 0.00931 0.00488 -0.0950 0.4918 0.9037
6.750 1.2831 0.00934 0.00489 -0.0954 0.4857 0.9047
7.000 1.3095 0.00933 0.00493 -0.0955 0.4780 0.9060
7.250 1.3336 0.00939 0.00498 -0.0952 0.4684 0.9073
7.500 1.3551 0.00957 0.00512 -0.0945 0.4481 0.9088
7.750 1.3709 0.01004 0.00545 -0.0929 0.4182 0.9105
8.000 1.3777 0.01092 0.00612 -0.0898 0.3779 0.9122
8.250 1.3768 0.01202 0.00700 -0.0855 0.3391 0.9142
8.500 1.3662 0.01311 0.00792 -0.0795 0.3060 0.9168
8.750 1.3461 0.01459 0.00923 -0.0724 0.2715 0.9197
9.000 1.3124 0.01688 0.01142 -0.0648 0.2389 0.9237
9.250 1.2891 0.01988 0.01442 -0.0607 0.2201 0.9273
9.500 1.2596 0.02403 0.01852 -0.0572 0.1970 0.9307
9.750 1.2264 0.02841 0.02280 -0.0535 0.1697 0.9334
10.000 1.2052 0.03176 0.02609 -0.0505 0.1485 0.9362
10.250 1.1826 0.03527 0.02952 -0.0476 0.1228 0.9391
10.500 1.1583 0.03910 0.03321 -0.0449 0.0900 0.9419
10.750 1.1312 0.04361 0.03752 -0.0426 0.0457 0.9442
11.000 1.1256 0.04655 0.04038 -0.0417 0.0254 0.9459
11.250 1.1214 0.04942 0.04322 -0.0408 0.0098 0.9479
11.500 1.1275 0.05137 0.04523 -0.0404 0.0085 0.9502
11.750 1.1353 0.05316 0.04708 -0.0401 0.0078 0.9526
12.000 1.1429 0.05504 0.04902 -0.0399 0.0076 0.9556
12.250 1.1491 0.05711 0.05116 -0.0397 0.0071 0.9589
12.500 1.1572 0.05907 0.05318 -0.0397 0.0068 0.9644
12.750 1.1624 0.06161 0.05580 -0.0400 0.0064 0.9713
13.000 1.1695 0.06410 0.05836 -0.0407 0.0062 0.9926
13.250 1.1727 0.06677 0.06110 -0.0408 0.0060 1.0000
13.500 1.1732 0.06986 0.06426 -0.0410 0.0058 1.0000
13.750 1.1760 0.07273 0.06720 -0.0413 0.0057 1.0000
14.000 1.1824 0.07523 0.06975 -0.0417 0.0056 1.0000
14.250 1.1878 0.07787 0.07245 -0.0421 0.0055 1.0000
14.500 1.1916 0.08073 0.07537 -0.0426 0.0054 1.0000
14.750 1.1947 0.08373 0.07843 -0.0431 0.0053 1.0000
15.000 1.1978 0.08676 0.08153 -0.0437 0.0051 1.0000
15.250 1.1996 0.09002 0.08486 -0.0443 0.0050 1.0000
15.500 1.2024 0.09315 0.08805 -0.0450 0.0049 1.0000
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