FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.28 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h80-il-1000000.txt Download as CSV file: xf-fx66h80-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5505 0.09005 0.08867 0.0216 1.0000 0.0065
-7.750 -0.5519 0.08623 0.08488 0.0193 1.0000 0.0072
-7.500 -0.5546 0.08232 0.08098 0.0160 0.9444 0.0071
-7.250 -0.5529 0.07865 0.07683 0.0132 0.7926 0.0072
-3.000 -0.2619 0.01368 0.00749 0.0107 0.5012 0.0095
-2.750 -0.2354 0.01288 0.00655 0.0111 0.4932 0.0103
-2.500 -0.2087 0.01213 0.00568 0.0116 0.4863 0.0110
-2.250 -0.1822 0.01131 0.00475 0.0122 0.4797 0.0113
-2.000 -0.1560 0.01062 0.00393 0.0127 0.4738 0.0116
-1.750 -0.1294 0.01019 0.00345 0.0131 0.4680 0.0123
-1.500 -0.1036 0.00961 0.00276 0.0138 0.4628 0.0123
-1.250 -0.0774 0.00913 0.00218 0.0144 0.4579 0.0124
-1.000 -0.0507 0.00882 0.00177 0.0148 0.4528 0.0128
-0.750 -0.0236 0.00864 0.00150 0.0152 0.4480 0.0140
-0.500 0.0026 0.00822 0.00120 0.0157 0.4442 0.0626
-0.250 0.0284 0.00786 0.00111 0.0160 0.4397 0.1574
0.000 0.0482 0.00678 0.00101 0.0171 0.4356 0.4871
0.250 0.0800 0.00536 0.00112 0.0166 0.4314 0.9630
0.500 0.1292 0.00555 0.00122 0.0122 0.4264 0.9795
0.750 0.1870 0.00579 0.00134 0.0058 0.4210 0.9895
1.000 0.2462 0.00589 0.00138 -0.0009 0.4161 0.9970
1.250 0.2894 0.00589 0.00131 -0.0043 0.4112 1.0000
1.500 0.3146 0.00594 0.00130 -0.0038 0.4072 1.0000
1.750 0.3400 0.00593 0.00129 -0.0033 0.4038 1.0000
2.000 0.3654 0.00594 0.00129 -0.0028 0.3999 1.0000
2.250 0.3908 0.00598 0.00129 -0.0023 0.3955 1.0000
2.500 0.4162 0.00602 0.00131 -0.0019 0.3918 1.0000
2.750 0.4418 0.00603 0.00133 -0.0014 0.3881 1.0000
3.000 0.4675 0.00607 0.00136 -0.0010 0.3840 1.0000
3.250 0.4930 0.00614 0.00142 -0.0005 0.3796 1.0000
3.500 0.5188 0.00616 0.00146 -0.0001 0.3757 1.0000
3.750 0.5445 0.00621 0.00151 0.0003 0.3716 1.0000
4.000 0.5700 0.00629 0.00158 0.0008 0.3671 1.0000
4.250 0.5957 0.00634 0.00166 0.0012 0.3630 1.0000
4.500 0.6214 0.00639 0.00174 0.0016 0.3558 1.0000
4.750 0.6471 0.00645 0.00181 0.0020 0.3460 1.0000
5.000 0.6726 0.00654 0.00186 0.0024 0.3301 1.0000
5.250 0.6980 0.00669 0.00196 0.0028 0.3097 1.0000
5.500 0.7233 0.00687 0.00209 0.0032 0.2898 1.0000
5.750 0.7483 0.00714 0.00230 0.0036 0.2629 1.0000
6.000 0.7706 0.00807 0.00279 0.0040 0.1708 1.0000
6.250 0.7888 0.00997 0.00397 0.0045 0.0275 1.0000
6.500 0.8127 0.01047 0.00448 0.0051 0.0180 1.0000
6.750 0.8369 0.01084 0.00489 0.0056 0.0151 1.0000
7.000 0.8592 0.01172 0.00595 0.0064 0.0111 1.0000
7.250 0.8834 0.01202 0.00627 0.0069 0.0103 1.0000
7.500 0.9073 0.01236 0.00663 0.0073 0.0087 1.0000
7.750 0.9287 0.01321 0.00756 0.0081 0.0067 1.0000
8.000 0.9489 0.01424 0.00873 0.0089 0.0060 1.0000
8.250 0.9707 0.01489 0.00946 0.0096 0.0056 1.0000
8.500 0.9913 0.01572 0.01038 0.0104 0.0052 1.0000
8.750 1.0116 0.01650 0.01125 0.0112 0.0048 1.0000
9.000 1.0322 0.01722 0.01204 0.0119 0.0044 1.0000
9.250 1.0511 0.01810 0.01299 0.0127 0.0041 1.0000
9.500 1.0663 0.01943 0.01442 0.0138 0.0037 1.0000
9.750 1.0606 0.02357 0.01886 0.0171 0.0033 1.0000
10.000 1.0732 0.02514 0.02056 0.0185 0.0033 1.0000
10.250 1.0824 0.02714 0.02273 0.0200 0.0033 1.0000
10.500 1.0881 0.02956 0.02534 0.0217 0.0033 1.0000
10.750 1.0878 0.03243 0.02843 0.0236 0.0032 1.0000
11.000 1.0757 0.03634 0.03256 0.0260 0.0034 1.0000
11.250 1.0753 0.03852 0.03487 0.0261 0.0034 1.0000
11.500 1.0719 0.04160 0.03811 0.0254 0.0034 1.0000
11.750 1.0682 0.04497 0.04162 0.0241 0.0035 1.0000
12.000 1.0676 0.04797 0.04474 0.0226 0.0035 1.0000
12.250 1.0655 0.05137 0.04827 0.0208 0.0036 1.0000
12.500 1.0583 0.05569 0.05274 0.0187 0.0036 1.0000
13.750 0.8058 0.09252 0.09065 0.0050 0.0049 1.0000
14.000 0.7901 0.09985 0.09807 0.0011 0.0048 1.0000
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Polar data table (+)
Polar graphs
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