FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 500,000 Max Cl/Cd: 98.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61163-il-500000-n5.txt Download as CSV file: xf-fx61163-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6236 0.05884 0.05593 -0.0661 1.0001 0.0052
-12.000 -0.6492 0.05279 0.04966 -0.0681 1.0001 0.0052
-11.750 -0.6689 0.04815 0.04483 -0.0688 1.0001 0.0052
-11.500 -0.6846 0.04439 0.04089 -0.0685 1.0001 0.0052
-11.250 -0.6923 0.04076 0.03705 -0.0690 0.9969 0.0052
-11.000 -0.6919 0.03746 0.03354 -0.0701 0.9764 0.0053
-10.750 -0.6496 0.03302 0.02870 -0.0806 0.9289 0.0054
-10.500 -0.6120 0.03007 0.02521 -0.0874 0.8522 0.0055
-10.250 -0.6019 0.02856 0.02333 -0.0867 0.8057 0.0056
-10.000 -0.5903 0.02717 0.02164 -0.0860 0.7766 0.0058
-9.750 -0.5769 0.02590 0.02012 -0.0852 0.7546 0.0059
-9.500 -0.5599 0.02469 0.01867 -0.0849 0.7374 0.0060
-9.250 -0.5413 0.02355 0.01732 -0.0845 0.7234 0.0062
-9.000 -0.5216 0.02249 0.01608 -0.0842 0.7115 0.0064
-8.750 -0.5011 0.02154 0.01496 -0.0838 0.7012 0.0065
-8.250 -0.4583 0.01984 0.01298 -0.0832 0.6829 0.0068
-8.000 -0.4363 0.01910 0.01210 -0.0830 0.6753 0.0070
-7.750 -0.4126 0.01851 0.01142 -0.0830 0.6683 0.0072
-7.500 -0.3907 0.01770 0.01051 -0.0829 0.6623 0.0075
-7.250 -0.3678 0.01695 0.00970 -0.0830 0.6571 0.0078
-7.000 -0.3436 0.01633 0.00902 -0.0832 0.6517 0.0081
-6.750 -0.3189 0.01574 0.00836 -0.0834 0.6468 0.0083
-6.500 -0.2932 0.01518 0.00773 -0.0838 0.6422 0.0085
-6.250 -0.2670 0.01466 0.00715 -0.0842 0.6375 0.0088
-6.000 -0.2401 0.01420 0.00662 -0.0847 0.6334 0.0092
-5.750 -0.2128 0.01379 0.00613 -0.0852 0.6299 0.0097
-5.500 -0.1847 0.01342 0.00571 -0.0858 0.6263 0.0102
-5.250 -0.1565 0.01301 0.00524 -0.0864 0.6226 0.0111
-5.000 -0.1279 0.01271 0.00489 -0.0870 0.6189 0.0124
-4.500 -0.0698 0.01211 0.00424 -0.0884 0.6125 0.0224
-4.250 -0.0401 0.01166 0.00392 -0.0894 0.6092 0.0533
-3.750 0.0268 0.00959 0.00288 -0.0949 0.6023 0.3375
-3.500 0.0650 0.00860 0.00261 -0.0986 0.5993 0.5323
-3.250 0.0959 0.00858 0.00270 -0.0993 0.5962 0.5760
-3.000 0.1260 0.00865 0.00275 -0.0997 0.5930 0.5960
-2.750 0.1557 0.00872 0.00277 -0.1001 0.5900 0.6055
-2.500 0.1858 0.00876 0.00272 -0.1007 0.5873 0.6117
-2.250 0.2153 0.00881 0.00272 -0.1011 0.5846 0.6153
-2.000 0.2451 0.00884 0.00273 -0.1015 0.5813 0.6198
-1.750 0.2751 0.00888 0.00271 -0.1020 0.5776 0.6246
-1.500 0.3048 0.00892 0.00269 -0.1025 0.5739 0.6284
-1.250 0.3339 0.00899 0.00271 -0.1028 0.5708 0.6315
-1.000 0.3636 0.00903 0.00274 -0.1032 0.5680 0.6349
-0.750 0.3935 0.00906 0.00275 -0.1037 0.5651 0.6382
-0.500 0.4234 0.00910 0.00274 -0.1043 0.5619 0.6412
-0.250 0.4527 0.00914 0.00276 -0.1047 0.5587 0.6434
0.000 0.4818 0.00921 0.00280 -0.1050 0.5559 0.6456
0.250 0.5112 0.00925 0.00284 -0.1054 0.5528 0.6479
0.500 0.5407 0.00929 0.00288 -0.1058 0.5487 0.6503
0.750 0.5700 0.00934 0.00291 -0.1062 0.5444 0.6529
1.000 0.5993 0.00941 0.00293 -0.1067 0.5408 0.6555
1.250 0.6289 0.00945 0.00298 -0.1072 0.5374 0.6576
1.500 0.6579 0.00949 0.00306 -0.1075 0.5338 0.6595
1.750 0.6868 0.00955 0.00313 -0.1078 0.5299 0.6614
2.000 0.7155 0.00963 0.00319 -0.1081 0.5262 0.6634
2.250 0.7447 0.00968 0.00327 -0.1085 0.5221 0.6656
2.500 0.7739 0.00974 0.00336 -0.1089 0.5179 0.6679
2.750 0.8027 0.00982 0.00342 -0.1093 0.5129 0.6700
3.000 0.8317 0.00988 0.00349 -0.1097 0.5072 0.6719
3.250 0.8601 0.00994 0.00359 -0.1099 0.5009 0.6734
3.500 0.8882 0.01003 0.00369 -0.1101 0.4961 0.6750
3.750 0.9167 0.01010 0.00381 -0.1104 0.4897 0.6768
4.000 0.9444 0.01021 0.00392 -0.1105 0.4816 0.6786
4.250 0.9726 0.01030 0.00404 -0.1107 0.4725 0.6804
4.500 1.0004 0.01042 0.00417 -0.1109 0.4646 0.6823
4.750 1.0276 0.01058 0.00430 -0.1110 0.4525 0.6843
5.000 1.0544 0.01076 0.00445 -0.1110 0.4367 0.6862
5.250 1.0805 0.01097 0.00464 -0.1109 0.4212 0.6878
5.500 1.1063 0.01120 0.00486 -0.1107 0.4061 0.6894
5.750 1.1317 0.01147 0.00511 -0.1105 0.3903 0.6910
6.000 1.1573 0.01173 0.00536 -0.1103 0.3770 0.6928
6.250 1.1827 0.01200 0.00563 -0.1101 0.3649 0.6947
6.750 1.2318 0.01267 0.00626 -0.1095 0.3335 0.6984
7.000 1.2536 0.01319 0.00667 -0.1088 0.3063 0.7002
7.250 1.2730 0.01386 0.00719 -0.1077 0.2716 0.7019
7.500 1.2900 0.01466 0.00780 -0.1063 0.2345 0.7034
7.750 1.3056 0.01553 0.00849 -0.1047 0.1964 0.7048
8.000 1.3199 0.01643 0.00924 -0.1029 0.1652 0.7063
8.250 1.3329 0.01737 0.01002 -0.1010 0.1353 0.7079
8.500 1.3447 0.01830 0.01083 -0.0988 0.1098 0.7098
8.750 1.3546 0.01914 0.01159 -0.0963 0.0908 0.7117
9.000 1.3637 0.02003 0.01242 -0.0937 0.0742 0.7136
9.500 1.3811 0.02205 0.01437 -0.0891 0.0513 0.7167
9.750 1.3901 0.02309 0.01545 -0.0871 0.0420 0.7182
10.250 1.3976 0.02618 0.01851 -0.0828 0.0232 0.7217
10.500 1.4057 0.02762 0.02002 -0.0816 0.0199 0.7237
10.750 1.4126 0.02929 0.02173 -0.0805 0.0172 0.7256
11.000 1.4209 0.03092 0.02344 -0.0797 0.0153 0.7274
11.250 1.4269 0.03284 0.02542 -0.0789 0.0128 0.7291
11.500 1.4321 0.03490 0.02753 -0.0782 0.0100 0.7308
11.750 1.4357 0.03714 0.02983 -0.0776 0.0070 0.7323
12.000 1.4372 0.03964 0.03240 -0.0769 0.0047 0.7339
12.250 1.4393 0.04209 0.03493 -0.0764 0.0040 0.7358
12.500 1.4413 0.04458 0.03752 -0.0758 0.0036 0.7378
12.750 1.4426 0.04717 0.04019 -0.0753 0.0033 0.7398
13.000 1.4433 0.04982 0.04294 -0.0749 0.0031 0.7418
13.250 1.4431 0.05258 0.04580 -0.0744 0.0029 0.7436
13.500 1.4428 0.05544 0.04875 -0.0741 0.0028 0.7454
13.750 1.4431 0.05825 0.05167 -0.0738 0.0027 0.7471
14.000 1.4432 0.06117 0.05470 -0.0737 0.0027 0.7488
14.250 1.4425 0.06426 0.05791 -0.0736 0.0026 0.7508
14.500 1.4410 0.06750 0.06126 -0.0737 0.0025 0.7528
14.750 1.4399 0.07075 0.06462 -0.0738 0.0025 0.7549
15.000 1.4379 0.07414 0.06813 -0.0740 0.0025 0.7570
15.250 1.4352 0.07773 0.07185 -0.0743 0.0024 0.7593
15.500 1.4318 0.08148 0.07571 -0.0748 0.0024 0.7615
15.750 1.4280 0.08533 0.07968 -0.0753 0.0023 0.7639
16.000 1.4239 0.08926 0.08374 -0.0759 0.0023 0.7665
16.250 1.4192 0.09336 0.08797 -0.0767 0.0022 0.7692
16.500 1.4144 0.09754 0.09226 -0.0776 0.0022 0.7720
16.750 1.4090 0.10187 0.09671 -0.0787 0.0022 0.7747
17.000 1.4031 0.10629 0.10126 -0.0798 0.0022 0.7774
17.250 1.3959 0.11101 0.10610 -0.0812 0.0021 0.7804
17.500 1.3890 0.11576 0.11098 -0.0827 0.0021 0.7836
17.750 1.3817 0.12063 0.11597 -0.0844 0.0021 0.7871
18.250 1.3673 0.13057 0.12616 -0.0883 0.0020 0.7947
18.500 1.3587 0.13587 0.13159 -0.0906 0.0020 0.7992
18.750 1.3516 0.14100 0.13684 -0.0930 0.0019 0.8041
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