FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 200,000 Max Cl/Cd: 62.78 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h80-il-200000-n5.txt Download as CSV file: xf-fx66h80-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5442 0.09450 0.09149 0.0196 1.0000 0.0218
-7.750 -0.5452 0.09085 0.08789 0.0157 1.0000 0.0222
-7.500 -0.5441 0.08710 0.08417 0.0121 1.0000 0.0224
-7.250 -0.5377 0.08303 0.08008 0.0086 1.0000 0.0225
-7.000 -0.5293 0.07886 0.07588 0.0057 1.0000 0.0227
-6.750 -0.5194 0.07467 0.07163 0.0034 1.0000 0.0227
-6.500 -0.5081 0.07044 0.06732 0.0015 1.0000 0.0228
-6.250 -0.4905 0.06595 0.06251 -0.0011 0.8340 0.0228
-6.000 -0.4791 0.06225 0.05851 -0.0012 0.7838 0.0229
-5.750 -0.4661 0.05838 0.05437 -0.0013 0.7494 0.0229
-5.250 -0.4200 0.03764 0.03334 0.0003 0.6630 0.0229
-4.750 -0.4101 0.03852 0.03330 0.0000 0.6630 0.0132
-4.500 -0.3907 0.03485 0.02923 0.0009 0.6457 0.0128
-4.250 -0.3697 0.03136 0.02529 0.0020 0.6303 0.0126
-4.000 -0.3474 0.02809 0.02150 0.0032 0.6162 0.0126
-3.750 -0.3238 0.02523 0.01813 0.0044 0.6033 0.0128
-3.500 -0.2974 0.02386 0.01628 0.0055 0.5904 0.0140
-3.250 -0.2744 0.02112 0.01311 0.0063 0.5790 0.0156
-3.000 -0.2482 0.01943 0.01104 0.0071 0.5680 0.0156
-2.500 -0.1949 0.01675 0.00780 0.0084 0.5483 0.0159
-2.250 -0.1686 0.01575 0.00663 0.0091 0.5394 0.0164
-2.000 -0.1428 0.01493 0.00564 0.0097 0.5313 0.0171
-1.750 -0.1171 0.01425 0.00486 0.0103 0.5232 0.0183
-1.250 -0.0655 0.01322 0.00360 0.0115 0.5089 0.0270
-1.000 -0.0396 0.01284 0.00315 0.0121 0.5027 0.0444
-0.750 -0.0152 0.01218 0.00284 0.0126 0.4961 0.1394
-0.500 0.0557 0.00974 0.00295 0.0043 0.4880 0.9717
-0.250 0.1276 0.00984 0.00275 -0.0049 0.4795 1.0000
0.000 0.1527 0.00988 0.00261 -0.0044 0.4745 1.0000
0.250 0.1780 0.00990 0.00253 -0.0039 0.4687 1.0000
0.500 0.2031 0.00996 0.00246 -0.0034 0.4638 1.0000
0.750 0.2284 0.01002 0.00242 -0.0029 0.4589 1.0000
1.000 0.2537 0.01007 0.00240 -0.0024 0.4536 1.0000
1.250 0.2789 0.01016 0.00238 -0.0019 0.4492 1.0000
1.500 0.3043 0.01023 0.00241 -0.0014 0.4446 1.0000
1.750 0.3297 0.01031 0.00244 -0.0009 0.4396 1.0000
2.000 0.3550 0.01042 0.00249 -0.0005 0.4354 1.0000
2.250 0.3805 0.01051 0.00257 0.0000 0.4306 1.0000
2.500 0.4060 0.01061 0.00266 0.0004 0.4260 1.0000
2.750 0.4314 0.01073 0.00274 0.0009 0.4220 1.0000
3.000 0.4569 0.01085 0.00287 0.0013 0.4174 1.0000
3.250 0.4825 0.01096 0.00304 0.0017 0.4125 1.0000
3.500 0.5079 0.01110 0.00317 0.0022 0.4085 1.0000
3.750 0.5335 0.01125 0.00335 0.0026 0.4041 1.0000
4.000 0.5591 0.01138 0.00354 0.0030 0.3992 1.0000
4.250 0.5845 0.01154 0.00372 0.0034 0.3949 1.0000
4.500 0.6101 0.01170 0.00400 0.0038 0.3906 1.0000
4.750 0.6358 0.01186 0.00426 0.0042 0.3856 1.0000
5.000 0.6612 0.01204 0.00449 0.0047 0.3812 1.0000
5.250 0.6868 0.01223 0.00479 0.0050 0.3766 1.0000
5.500 0.7124 0.01240 0.00509 0.0054 0.3709 1.0000
5.750 0.7377 0.01242 0.00525 0.0059 0.3570 1.0000
6.000 0.7627 0.01240 0.00529 0.0064 0.3324 1.0000
6.250 0.7873 0.01254 0.00539 0.0069 0.2935 1.0000
6.500 0.8079 0.01354 0.00586 0.0072 0.1817 1.0000
6.750 0.8221 0.01610 0.00760 0.0076 0.0408 1.0000
7.000 0.8433 0.01715 0.00870 0.0082 0.0275 1.0000
7.250 0.8646 0.01805 0.00978 0.0088 0.0218 1.0000
7.500 0.8835 0.01934 0.01126 0.0095 0.0183 1.0000
7.750 0.9025 0.02049 0.01260 0.0103 0.0166 1.0000
8.000 0.9203 0.02168 0.01394 0.0111 0.0145 1.0000
8.250 0.9372 0.02289 0.01523 0.0118 0.0124 1.0000
8.500 0.9449 0.02524 0.01769 0.0133 0.0111 1.0000
8.750 0.9594 0.02665 0.01922 0.0145 0.0106 1.0000
9.000 0.9724 0.02827 0.02097 0.0159 0.0101 1.0000
9.250 0.9849 0.03002 0.02286 0.0173 0.0096 1.0000
9.500 0.9972 0.03193 0.02498 0.0187 0.0092 1.0000
9.750 1.0086 0.03407 0.02730 0.0202 0.0089 1.0000
10.000 1.0188 0.03621 0.02965 0.0214 0.0086 1.0000
10.250 1.0263 0.03829 0.03191 0.0226 0.0081 1.0000
10.500 1.0285 0.04016 0.03395 0.0238 0.0077 1.0000
10.750 1.0283 0.04202 0.03591 0.0241 0.0072 1.0000
11.000 1.0277 0.04462 0.03866 0.0239 0.0069 1.0000
11.250 1.0261 0.04763 0.04183 0.0234 0.0067 1.0000
11.500 1.0171 0.05183 0.04619 0.0224 0.0063 1.0000
11.750 1.0082 0.05619 0.05076 0.0210 0.0062 1.0000
12.000 1.0012 0.06033 0.05510 0.0193 0.0062 1.0000
12.250 0.9914 0.06504 0.06000 0.0171 0.0062 1.0000
12.500 0.9806 0.07002 0.06516 0.0146 0.0062 1.0000
13.000 0.9557 0.08105 0.07652 0.0086 0.0062 1.0000
13.250 0.9415 0.08720 0.08283 0.0052 0.0062 1.0000
13.500 0.9279 0.09350 0.08925 0.0016 0.0062 1.0000
13.750 0.9134 0.10062 0.09652 -0.0027 0.0062 1.0000
14.000 0.7818 0.10334 0.09970 0.0001 0.0071 1.0000
14.250 0.7348 0.11715 0.11376 -0.0074 0.0083 1.0000
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Polar data table (+)
Polar graphs
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