FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.1 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h60-il-1000000.txt Download as CSV file: xf-fx66h60-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-60
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 -0.6097 0.09229 0.09082 0.0277 1.0000 0.0059
-7.750 -0.6096 0.08845 0.08700 0.0251 1.0000 0.0062
-7.500 -0.6096 0.08508 0.08365 0.0216 1.0000 0.0067
-7.250 -0.6063 0.08073 0.07928 0.0185 1.0000 0.0067
-7.000 -0.5972 0.07677 0.07529 0.0153 1.0000 0.0069
-6.750 -0.5874 0.07278 0.07125 0.0131 1.0000 0.0070
-6.500 -0.5762 0.06871 0.06710 0.0113 1.0000 0.0071
-6.250 -0.5640 0.06466 0.06299 0.0100 1.0000 0.0071
-6.000 -0.5502 0.06063 0.05888 0.0090 1.0000 0.0071
-5.750 -0.5351 0.05665 0.05480 0.0083 1.0000 0.0071
-5.500 -0.5187 0.05274 0.05080 0.0080 1.0000 0.0071
-5.250 -0.5012 0.04893 0.04686 0.0080 1.0000 0.0072
-5.000 -0.4828 0.04521 0.04301 0.0082 1.0000 0.0072
-4.750 -0.4635 0.04161 0.03927 0.0087 1.0000 0.0072
-4.500 -0.4434 0.03805 0.03555 0.0095 1.0000 0.0072
-4.250 -0.4227 0.03464 0.03197 0.0104 1.0000 0.0072
-4.000 -0.4013 0.03129 0.02842 0.0115 1.0000 0.0072
-3.750 -0.3795 0.02812 0.02504 0.0128 1.0000 0.0072
-3.500 -0.3364 0.01987 0.01598 0.0095 0.8902 0.0078
-3.250 -0.3180 0.01818 0.01366 0.0117 0.7719 0.0084
-3.000 -0.2954 0.01715 0.01226 0.0128 0.7074 0.0092
-2.750 -0.2708 0.01631 0.01109 0.0137 0.6549 0.0109
-1.750 -0.1665 0.01113 0.00480 0.0173 0.5211 0.0120
-1.250 -0.1168 0.00913 0.00244 0.0193 0.4763 0.0107
-0.750 -0.0646 0.00850 0.00152 0.0204 0.4376 0.0135
-0.500 -0.0382 0.00824 0.00111 0.0209 0.4196 0.0181
-0.250 -0.0127 0.00783 0.00095 0.0214 0.4042 0.1191
0.000 -0.0080 0.00530 0.00082 0.0255 0.3941 0.8634
0.250 0.0146 0.00531 0.00086 0.0271 0.3811 0.9152
0.500 0.0361 0.00535 0.00092 0.0291 0.3688 0.9464
0.750 0.0613 0.00544 0.00095 0.0301 0.3568 0.9623
1.000 0.0950 0.00559 0.00103 0.0292 0.3450 0.9744
1.250 0.1401 0.00583 0.00116 0.0257 0.3327 0.9825
1.500 0.1748 0.00591 0.00116 0.0242 0.3221 0.9835
1.750 0.2069 0.00596 0.00116 0.0232 0.3125 0.9843
2.000 0.2386 0.00603 0.00117 0.0223 0.3034 0.9853
2.500 0.3007 0.00616 0.00124 0.0208 0.2874 0.9874
2.750 0.3314 0.00625 0.00128 0.0200 0.2800 0.9886
3.000 0.3619 0.00631 0.00133 0.0194 0.2728 0.9900
3.250 0.3917 0.00640 0.00139 0.0189 0.2659 0.9914
3.500 0.4213 0.00647 0.00147 0.0185 0.2597 0.9928
3.750 0.4505 0.00659 0.00159 0.0181 0.2536 0.9943
4.000 0.4822 0.00665 0.00167 0.0172 0.2482 0.9952
4.250 0.5132 0.00674 0.00175 0.0163 0.2376 0.9962
4.750 0.5745 0.00697 0.00194 0.0148 0.2118 0.9986
5.000 0.6047 0.00719 0.00208 0.0141 0.1823 0.9996
5.250 0.6274 0.00804 0.00249 0.0145 0.0907 1.0000
5.500 0.6453 0.00917 0.00330 0.0160 0.0131 1.0000
5.750 0.6654 0.00986 0.00414 0.0177 0.0075 1.0000
6.000 0.6857 0.01040 0.00480 0.0191 0.0067 1.0000
6.250 0.7058 0.01108 0.00562 0.0206 0.0064 1.0000
6.500 0.7269 0.01172 0.00636 0.0218 0.0059 1.0000
6.750 0.7489 0.01234 0.00709 0.0228 0.0054 1.0000
7.000 0.7701 0.01321 0.00808 0.0238 0.0052 1.0000
7.250 0.7915 0.01412 0.00909 0.0248 0.0049 1.0000
7.500 0.8127 0.01515 0.01021 0.0256 0.0046 1.0000
7.750 0.8269 0.01794 0.01319 0.0272 0.0040 1.0000
8.000 0.8475 0.01941 0.01485 0.0281 0.0035 1.0000
8.250 0.8662 0.02151 0.01716 0.0292 0.0034 1.0000
8.500 0.8806 0.02487 0.02084 0.0304 0.0034 1.0000
8.750 0.8906 0.03116 0.02771 0.0328 0.0054 1.0000
9.000 0.9018 0.03426 0.03107 0.0335 0.0053 1.0000
9.250 0.9102 0.03728 0.03434 0.0339 0.0051 1.0000
9.500 0.9143 0.04051 0.03781 0.0341 0.0050 1.0000
9.750 0.9130 0.04391 0.04141 0.0340 0.0049 1.0000
10.000 0.9053 0.04717 0.04485 0.0337 0.0048 1.0000
10.250 0.8885 0.05120 0.04900 0.0308 0.0048 1.0000
10.500 0.8737 0.05734 0.05529 0.0247 0.0049 1.0000
10.750 0.8607 0.06386 0.06192 0.0186 0.0049 1.0000
11.000 0.8410 0.07242 0.07060 0.0118 0.0052 1.0000
11.250 0.8249 0.08028 0.07853 0.0059 0.0052 1.0000
11.500 0.8020 0.09037 0.08871 -0.0007 0.0057 1.0000
11.750 0.7828 0.10020 0.09858 -0.0063 0.0058 1.0000
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Polar data table (+)
Polar graphs
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