FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 500,000 Max Cl/Cd: 87.56 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h80-il-500000.txt Download as CSV file: xf-fx66h80-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5466 0.09195 0.09003 0.0221 1.0000 0.0118
-7.750 -0.5467 0.08814 0.08626 0.0192 1.0000 0.0128
-7.500 -0.5499 0.08449 0.08263 0.0165 1.0000 0.0129
-7.250 -0.5473 0.08041 0.07855 0.0130 1.0000 0.0132
-7.000 -0.5354 0.07649 0.07461 0.0086 1.0000 0.0138
-6.750 -0.5246 0.07236 0.07043 0.0059 1.0000 0.0139
-6.500 -0.5124 0.06809 0.06610 0.0036 1.0000 0.0140
-6.250 -0.4935 0.06334 0.06123 0.0003 0.9290 0.0140
-6.000 -0.4824 0.05983 0.05725 0.0004 0.8093 0.0141
-5.750 -0.4684 0.03966 0.03686 0.0022 0.7111 0.0148
-5.500 -0.4571 0.03536 0.03237 0.0019 0.6863 0.0152
-5.250 -0.4427 0.03168 0.02850 0.0017 0.6638 0.0156
-5.000 -0.4265 0.02824 0.02485 0.0016 0.6434 0.0161
-4.750 -0.4086 0.02490 0.02129 0.0017 0.6261 0.0168
-4.500 -0.3976 0.03631 0.03216 0.0007 0.6343 0.0175
-4.250 -0.3758 0.03348 0.02901 0.0014 0.6168 0.0187
-4.000 -0.3521 0.03082 0.02602 0.0024 0.6011 0.0205
-3.750 -0.3221 0.03064 0.02551 0.0036 0.5856 0.0228
-3.500 -0.2985 0.02851 0.02301 0.0047 0.5728 0.0229
-3.250 -0.2820 0.02241 0.01638 0.0061 0.5638 0.0248
-3.000 -0.2578 0.02070 0.01449 0.0067 0.5530 0.0263
-2.750 -0.2304 0.01801 0.01134 0.0083 0.5441 0.0205
-2.500 -0.2037 0.01538 0.00832 0.0096 0.5353 0.0182
-2.250 -0.1767 0.01453 0.00726 0.0101 0.5269 0.0196
-2.000 -0.1498 0.01336 0.00591 0.0107 0.5191 0.0194
-1.750 -0.1236 0.01223 0.00463 0.0115 0.5120 0.0186
-1.500 -0.0980 0.01143 0.00371 0.0123 0.5054 0.0184
-1.250 -0.0722 0.01085 0.00304 0.0130 0.4991 0.0192
-1.000 -0.0460 0.01044 0.00252 0.0136 0.4929 0.0214
-0.750 -0.0204 0.00988 0.00194 0.0144 0.4876 0.0521
-0.500 0.0020 0.00894 0.00177 0.0151 0.4821 0.2797
-0.250 0.0714 0.00713 0.00206 0.0068 0.4749 0.9806
0.000 0.1531 0.00729 0.00202 -0.0047 0.4670 0.9991
0.250 0.1824 0.00734 0.00194 -0.0050 0.4622 1.0000
0.500 0.2075 0.00734 0.00189 -0.0045 0.4573 1.0000
0.750 0.2328 0.00735 0.00184 -0.0040 0.4525 1.0000
1.000 0.2579 0.00743 0.00181 -0.0035 0.4482 1.0000
1.250 0.2834 0.00743 0.00180 -0.0030 0.4438 1.0000
1.500 0.3088 0.00746 0.00179 -0.0025 0.4394 1.0000
1.750 0.3342 0.00755 0.00180 -0.0020 0.4350 1.0000
2.000 0.3598 0.00758 0.00183 -0.0016 0.4305 1.0000
2.250 0.3853 0.00762 0.00186 -0.0011 0.4261 1.0000
2.500 0.4107 0.00771 0.00190 -0.0007 0.4221 1.0000
2.750 0.4363 0.00778 0.00197 -0.0002 0.4178 1.0000
3.000 0.4619 0.00783 0.00203 0.0002 0.4131 1.0000
3.250 0.4874 0.00792 0.00212 0.0007 0.4089 1.0000
3.500 0.5129 0.00802 0.00222 0.0011 0.4048 1.0000
3.750 0.5386 0.00809 0.00232 0.0015 0.4002 1.0000
4.000 0.5641 0.00818 0.00242 0.0020 0.3957 1.0000
4.250 0.5897 0.00831 0.00256 0.0024 0.3915 1.0000
4.500 0.6155 0.00839 0.00273 0.0028 0.3868 1.0000
4.750 0.6410 0.00850 0.00286 0.0032 0.3822 1.0000
5.000 0.6667 0.00854 0.00295 0.0037 0.3739 1.0000
5.250 0.6922 0.00856 0.00300 0.0041 0.3633 1.0000
5.500 0.7179 0.00855 0.00303 0.0045 0.3479 1.0000
5.750 0.7434 0.00862 0.00310 0.0049 0.3242 1.0000
6.000 0.7688 0.00878 0.00326 0.0053 0.3019 1.0000
6.250 0.7930 0.00920 0.00353 0.0057 0.2540 1.0000
6.500 0.8066 0.01212 0.00527 0.0061 0.0343 1.0000
6.750 0.8296 0.01287 0.00609 0.0068 0.0240 1.0000
7.000 0.8506 0.01403 0.00741 0.0076 0.0186 1.0000
7.250 0.8738 0.01457 0.00806 0.0082 0.0164 1.0000
7.500 0.8951 0.01547 0.00906 0.0089 0.0141 1.0000
7.750 0.9123 0.01699 0.01071 0.0099 0.0121 1.0000
8.000 0.9204 0.01982 0.01373 0.0120 0.0110 1.0000
8.250 0.9431 0.02021 0.01420 0.0126 0.0102 1.0000
8.500 0.9624 0.02109 0.01516 0.0136 0.0093 1.0000
8.750 0.9786 0.02244 0.01662 0.0148 0.0087 1.0000
9.000 0.9944 0.02387 0.01815 0.0161 0.0082 1.0000
9.250 1.0091 0.02551 0.01994 0.0175 0.0078 1.0000
9.500 1.0233 0.02722 0.02178 0.0188 0.0075 1.0000
9.750 1.0356 0.02905 0.02370 0.0200 0.0070 1.0000
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