FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.45 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h80-il-1000000-n5.txt Download as CSV file: xf-fx66h80-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-80
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5658 0.08436 0.08181 0.0180 0.5878 0.0038
-7.500 -0.5706 0.08058 0.07800 0.0157 0.5776 0.0038
-7.250 -0.5687 0.07608 0.07346 0.0125 0.5684 0.0037
-7.000 -0.5641 0.07112 0.06843 0.0094 0.5596 0.0040
-6.750 -0.5565 0.06622 0.06345 0.0068 0.5511 0.0041
-6.500 -0.5461 0.06116 0.05827 0.0046 0.5429 0.0043
-6.250 -0.5335 0.05641 0.05339 0.0031 0.5342 0.0043
-6.000 -0.5173 0.05215 0.04899 0.0022 0.5255 0.0045
-5.000 -0.4489 0.03331 0.02923 0.0029 0.4972 0.0045
-4.750 -0.4313 0.02757 0.02308 0.0046 0.4916 0.0043
-4.500 -0.4172 0.01873 0.01338 0.0083 0.4882 0.0043
-4.250 -0.3944 0.01582 0.00998 0.0097 0.4816 0.0044
-4.000 -0.3689 0.01464 0.00855 0.0103 0.4747 0.0046
-3.750 -0.3443 0.01291 0.00650 0.0112 0.4687 0.0050
-3.250 -0.2919 0.01168 0.00502 0.0120 0.4568 0.0058
-3.000 -0.2654 0.01124 0.00449 0.0123 0.4511 0.0061
-2.750 -0.2389 0.01079 0.00395 0.0127 0.4462 0.0063
-2.500 -0.2125 0.01035 0.00342 0.0132 0.4413 0.0066
-2.250 -0.1859 0.01003 0.00304 0.0135 0.4365 0.0070
-2.000 -0.1591 0.00975 0.00269 0.0138 0.4322 0.0074
-1.750 -0.1325 0.00941 0.00228 0.0142 0.4278 0.0075
-1.500 -0.1057 0.00913 0.00192 0.0146 0.4236 0.0077
-1.250 -0.0786 0.00892 0.00163 0.0149 0.4197 0.0079
-1.000 -0.0514 0.00876 0.00142 0.0151 0.4156 0.0082
-0.750 -0.0242 0.00858 0.00120 0.0154 0.4116 0.0121
-0.500 0.0031 0.00846 0.00109 0.0156 0.4080 0.0231
-0.250 0.0304 0.00834 0.00101 0.0158 0.4047 0.0403
0.000 0.0573 0.00816 0.00095 0.0160 0.4008 0.0813
0.250 0.0822 0.00768 0.00090 0.0164 0.3968 0.2309
0.500 0.0909 0.00578 0.00076 0.0198 0.3939 0.7850
0.750 0.1212 0.00541 0.00086 0.0198 0.3908 0.9440
1.000 0.1727 0.00554 0.00096 0.0147 0.3863 0.9733
1.250 0.2134 0.00570 0.00105 0.0121 0.3817 0.9842
1.500 0.2571 0.00578 0.00108 0.0086 0.3775 0.9877
1.750 0.2892 0.00582 0.00109 0.0077 0.3736 0.9893
2.000 0.3198 0.00587 0.00109 0.0071 0.3697 0.9906
2.250 0.3500 0.00592 0.00112 0.0065 0.3655 0.9920
2.500 0.3799 0.00596 0.00114 0.0061 0.3617 0.9933
2.750 0.4093 0.00602 0.00118 0.0057 0.3574 0.9944
3.000 0.4399 0.00607 0.00121 0.0051 0.3534 0.9953
3.250 0.4707 0.00611 0.00127 0.0044 0.3495 0.9961
3.500 0.5012 0.00616 0.00131 0.0037 0.3446 0.9970
3.750 0.5314 0.00623 0.00137 0.0031 0.3403 0.9979
4.000 0.5619 0.00628 0.00144 0.0025 0.3363 0.9988
4.250 0.5924 0.00635 0.00151 0.0018 0.3314 0.9996
4.500 0.6210 0.00644 0.00162 0.0016 0.3219 1.0000
4.750 0.6464 0.00657 0.00171 0.0020 0.3064 1.0000
5.000 0.6714 0.00682 0.00184 0.0024 0.2764 1.0000
5.250 0.6956 0.00730 0.00209 0.0027 0.2239 1.0000
5.500 0.7179 0.00829 0.00264 0.0031 0.1305 1.0000
5.750 0.7403 0.00921 0.00326 0.0035 0.0587 1.0000
6.000 0.7636 0.00983 0.00373 0.0040 0.0244 1.0000
6.250 0.7880 0.01016 0.00405 0.0045 0.0167 1.0000
6.500 0.8122 0.01050 0.00440 0.0050 0.0127 1.0000
6.750 0.8366 0.01081 0.00475 0.0055 0.0105 1.0000
7.000 0.8609 0.01112 0.00511 0.0059 0.0092 1.0000
7.250 0.8848 0.01149 0.00550 0.0064 0.0078 1.0000
7.500 0.9083 0.01197 0.00603 0.0070 0.0062 1.0000
7.750 0.9323 0.01229 0.00638 0.0074 0.0054 1.0000
8.000 0.9559 0.01268 0.00680 0.0079 0.0045 1.0000
8.250 0.9789 0.01318 0.00732 0.0084 0.0037 1.0000
8.500 1.0011 0.01382 0.00805 0.0091 0.0032 1.0000
8.750 1.0237 0.01433 0.00865 0.0096 0.0030 1.0000
9.000 1.0457 0.01491 0.00931 0.0102 0.0028 1.0000
9.250 1.0670 0.01559 0.01008 0.0108 0.0026 1.0000
9.500 1.0879 0.01627 0.01084 0.0115 0.0024 1.0000
9.750 1.1087 0.01693 0.01156 0.0121 0.0022 1.0000
10.000 1.1286 0.01768 0.01238 0.0128 0.0021 1.0000
10.250 1.1475 0.01851 0.01329 0.0135 0.0019 1.0000
10.500 1.1648 0.01947 0.01435 0.0143 0.0018 1.0000
10.750 1.1751 0.02116 0.01620 0.0156 0.0016 1.0000
11.000 1.1810 0.02314 0.01838 0.0172 0.0015 1.0000
11.250 1.1907 0.02456 0.01994 0.0183 0.0015 1.0000
11.500 1.1997 0.02590 0.02140 0.0193 0.0014 1.0000
11.750 1.1980 0.02784 0.02346 0.0204 0.0014 1.0000
12.000 1.1985 0.03053 0.02628 0.0194 0.0014 1.0000
12.250 1.1965 0.03385 0.02976 0.0181 0.0014 1.0000
12.500 1.1970 0.03693 0.03296 0.0169 0.0014 1.0000
12.750 1.1945 0.04037 0.03654 0.0156 0.0014 1.0000
13.000 1.1922 0.04381 0.04010 0.0144 0.0013 1.0000
13.250 1.1843 0.04794 0.04439 0.0130 0.0013 1.0000
13.500 1.1783 0.05188 0.04845 0.0116 0.0013 1.0000
13.750 1.1705 0.05609 0.05280 0.0101 0.0013 1.0000
14.000 1.1632 0.06031 0.05714 0.0084 0.0013 1.0000
14.250 1.1494 0.06549 0.06247 0.0064 0.0013 1.0000
14.500 1.1343 0.07113 0.06825 0.0041 0.0013 1.0000
14.750 1.1230 0.07653 0.07378 0.0017 0.0013 1.0000
15.000 1.1081 0.08276 0.08015 -0.0012 0.0013 1.0000
15.250 1.0964 0.08871 0.08622 -0.0040 0.0013 1.0000
15.500 1.0769 0.09629 0.09394 -0.0075 0.0013 1.0000
15.750 1.0635 0.10295 0.10071 -0.0108 0.0013 1.0000
16.000 1.0445 0.11105 0.10894 -0.0147 0.0013 1.0000
16.250 1.0191 0.12092 0.11896 -0.0194 0.0013 1.0000
16.500 1.0030 0.12913 0.12726 -0.0234 0.0013 1.0000
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Polar data table (+)
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