WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 100,000 Max Cl/Cd: 34.23 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66a175-il-100000-n5.txt Download as CSV file: xf-fx66a175-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2195 0.09538 0.09001 -0.0753 0.7312 0.0214
-11.000 -0.2255 0.08890 0.08350 -0.0787 0.7215 0.0212
-10.750 -0.2723 0.07264 0.06718 -0.0890 0.7229 0.0194
-9.750 -0.3429 0.05241 0.04601 -0.1032 0.6897 0.0185
-9.500 -0.3566 0.04949 0.04283 -0.1036 0.6826 0.0185
-9.250 -0.3626 0.04668 0.03979 -0.1033 0.6753 0.0186
-9.000 -0.3625 0.04374 0.03657 -0.1032 0.6691 0.0190
-8.750 -0.3556 0.04161 0.03429 -0.1030 0.6621 0.0197
-8.500 -0.3444 0.03991 0.03237 -0.1028 0.6563 0.0207
-8.250 -0.3321 0.03804 0.03024 -0.1023 0.6502 0.0217
-8.000 -0.3180 0.03604 0.02790 -0.1017 0.6446 0.0227
-7.750 -0.3011 0.03398 0.02546 -0.1011 0.6397 0.0231
-7.500 -0.2819 0.03207 0.02323 -0.1004 0.6338 0.0238
-7.250 -0.2607 0.03044 0.02130 -0.0996 0.6286 0.0245
-7.000 -0.2386 0.02905 0.01967 -0.0988 0.6235 0.0254
-6.750 -0.2174 0.02768 0.01819 -0.0980 0.6183 0.0267
-6.500 -0.1974 0.02661 0.01709 -0.0973 0.6139 0.0291
-6.250 -0.1763 0.02579 0.01619 -0.0966 0.6093 0.0319
-6.000 -0.1556 0.02495 0.01525 -0.0956 0.6045 0.0343
-5.750 -0.1356 0.02410 0.01426 -0.0946 0.6005 0.0369
-5.500 -0.1151 0.02333 0.01337 -0.0939 0.5969 0.0423
-5.250 -0.0940 0.02258 0.01257 -0.0934 0.5923 0.0510
-5.000 -0.0728 0.02170 0.01168 -0.0929 0.5884 0.0684
-4.750 -0.0541 0.02032 0.01068 -0.0927 0.5852 0.1488
-4.500 -0.0387 0.01925 0.01087 -0.0916 0.5821 0.3883
-4.250 -0.0121 0.01983 0.01128 -0.0911 0.5781 0.4567
-4.000 0.0137 0.02058 0.01184 -0.0902 0.5746 0.4908
-3.750 0.0396 0.02121 0.01237 -0.0890 0.5715 0.5122
-3.500 0.0661 0.02156 0.01255 -0.0883 0.5690 0.5271
-3.250 0.0918 0.02172 0.01259 -0.0879 0.5654 0.5372
-3.000 0.1182 0.02175 0.01245 -0.0877 0.5619 0.5446
-2.750 0.1449 0.02173 0.01226 -0.0877 0.5587 0.5502
-2.500 0.1721 0.02172 0.01208 -0.0876 0.5560 0.5548
-2.250 0.1995 0.02167 0.01183 -0.0878 0.5533 0.5591
-2.000 0.2257 0.02166 0.01170 -0.0879 0.5498 0.5632
-1.750 0.2522 0.02168 0.01165 -0.0878 0.5468 0.5664
-1.500 0.2792 0.02169 0.01154 -0.0879 0.5442 0.5697
-1.250 0.3069 0.02169 0.01137 -0.0881 0.5419 0.5728
-1.000 0.3352 0.02170 0.01118 -0.0885 0.5400 0.5761
-0.750 0.3606 0.02180 0.01128 -0.0884 0.5370 0.5786
-0.500 0.3866 0.02190 0.01135 -0.0884 0.5342 0.5810
-0.250 0.4131 0.02199 0.01139 -0.0885 0.5317 0.5834
0.000 0.4403 0.02207 0.01138 -0.0886 0.5294 0.5860
0.250 0.4680 0.02214 0.01133 -0.0889 0.5273 0.5890
0.500 0.4960 0.02222 0.01130 -0.0892 0.5254 0.5921
0.750 0.5198 0.02246 0.01162 -0.0889 0.5222 0.5945
1.000 0.5449 0.02267 0.01186 -0.0888 0.5195 0.5972
1.250 0.5708 0.02286 0.01204 -0.0888 0.5172 0.5999
1.500 0.5976 0.02305 0.01218 -0.0889 0.5152 0.6029
1.750 0.6251 0.02321 0.01228 -0.0892 0.5133 0.6063
2.000 0.6528 0.02333 0.01239 -0.0894 0.5117 0.6092
2.250 0.6759 0.02368 0.01282 -0.0890 0.5090 0.6123
2.500 0.6985 0.02407 0.01329 -0.0886 0.5060 0.6157
2.750 0.7229 0.02439 0.01366 -0.0885 0.5034 0.6195
3.000 0.7480 0.02464 0.01395 -0.0883 0.5012 0.6229
3.250 0.7742 0.02484 0.01417 -0.0883 0.4993 0.6266
3.500 0.8012 0.02505 0.01438 -0.0885 0.4978 0.6306
3.750 0.8278 0.02536 0.01471 -0.0886 0.4963 0.6347
4.000 0.8449 0.02612 0.01568 -0.0876 0.4933 0.6385
4.250 0.8650 0.02674 0.01643 -0.0870 0.4905 0.6431
4.500 0.8875 0.02723 0.01700 -0.0866 0.4881 0.6485
4.750 0.9118 0.02759 0.01746 -0.0865 0.4861 0.6534
5.000 0.9378 0.02788 0.01782 -0.0865 0.4845 0.6591
5.250 0.9646 0.02818 0.01817 -0.0867 0.4831 0.6654
5.500 0.9847 0.02883 0.01901 -0.0861 0.4812 0.6718
6.000 1.0045 0.03126 0.02189 -0.0827 0.4748 0.6872
6.250 1.0225 0.03200 0.02279 -0.0819 0.4727 0.6981
6.500 1.0440 0.03250 0.02345 -0.0814 0.4710 0.7123
6.750 1.0684 0.03278 0.02393 -0.0812 0.4695 0.7324
7.250 1.0431 0.03728 0.02926 -0.0735 0.4601 1.0000
7.500 1.0501 0.03869 0.03072 -0.0718 0.4575 1.0000
7.750 1.0706 0.03937 0.03145 -0.0714 0.4559 1.0000
8.000 1.0981 0.03965 0.03178 -0.0716 0.4547 1.0000
9.000 0.9215 0.06588 0.05820 -0.0636 0.4140 1.0000
9.250 0.9448 0.06632 0.05871 -0.0634 0.4126 1.0000
9.500 0.9692 0.06668 0.05916 -0.0631 0.4115 1.0000
10.000 0.9628 0.07296 0.06557 -0.0627 0.3986 1.0000
10.500 0.9621 0.07874 0.07154 -0.0625 0.3860 1.0000
10.750 0.9859 0.07903 0.07196 -0.0621 0.3845 1.0000
11.250 0.9856 0.08492 0.07804 -0.0621 0.3715 1.0000
11.500 1.0110 0.08491 0.07817 -0.0617 0.3700 1.0000
12.000 1.0182 0.08968 0.08317 -0.0616 0.3566 1.0000
12.500 1.0621 0.08791 0.08175 -0.0599 0.3411 1.0000
13.000 1.0783 0.08830 0.08231 -0.0588 0.2977 1.0000
13.500 1.0777 0.09129 0.08347 -0.0574 0.0947 1.0000
13.750 1.0552 0.09764 0.08934 -0.0585 0.0463 1.0000
14.000 1.0469 0.10219 0.09372 -0.0592 0.0299 1.0000
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