FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 200,000 Max Cl/Cd: 62.97 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h80-il-200000.txt Download as CSV file: xf-fx66h80-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5413 0.09146 0.08851 0.0198 1.0000 0.0302
-7.500 -0.5420 0.08779 0.08489 0.0171 1.0000 0.0307
-7.250 -0.5418 0.08401 0.08114 0.0141 1.0000 0.0314
-7.000 -0.5366 0.07985 0.07697 0.0101 1.0000 0.0323
-6.750 -0.5266 0.07575 0.07282 0.0053 1.0000 0.0335
-6.500 -0.5117 0.07219 0.06909 0.0010 1.0000 0.0343
-6.250 -0.4971 0.06868 0.06542 -0.0007 1.0000 0.0346
-6.000 -0.4825 0.06503 0.06161 -0.0018 1.0000 0.0347
-5.750 -0.4791 0.05718 0.05381 -0.0029 1.0000 0.0359
-5.500 -0.4657 0.05358 0.05024 -0.0030 1.0000 0.0370
-5.250 -0.4493 0.05036 0.04699 -0.0034 1.0000 0.0387
-5.000 -0.4299 0.04706 0.04360 -0.0040 1.0000 0.0410
-4.500 -0.3814 0.04049 0.03575 -0.0041 0.7965 0.0487
-4.250 -0.3660 0.03749 0.03262 -0.0032 0.7584 0.0508
-4.000 -0.3463 0.03531 0.03016 -0.0023 0.7288 0.0545
-3.750 -0.3238 0.03301 0.02720 -0.0009 0.7063 0.0627
-3.500 -0.3030 0.03062 0.02471 -0.0004 0.6851 0.0672
-3.250 -0.2804 0.02861 0.02229 0.0006 0.6682 0.0782
-3.000 -0.2581 0.02710 0.02059 0.0011 0.6522 0.0949
-2.500 -0.1956 0.02031 0.01233 0.0054 0.6289 0.0414
-2.250 -0.1660 0.01892 0.01037 0.0067 0.6173 0.0353
-2.000 -0.1384 0.01769 0.00891 0.0073 0.6066 0.0344
-1.750 -0.1113 0.01636 0.00740 0.0080 0.5972 0.0344
-1.500 -0.0857 0.01490 0.00586 0.0089 0.5880 0.0361
-1.250 -0.0608 0.01400 0.00494 0.0097 0.5794 0.0421
-1.000 0.0569 0.01010 0.00395 -0.0078 0.5658 1.0000
-0.750 0.0817 0.01016 0.00374 -0.0071 0.5587 1.0000
-0.500 0.1069 0.01019 0.00361 -0.0066 0.5508 1.0000
-0.250 0.1318 0.01028 0.00348 -0.0060 0.5445 1.0000
0.000 0.1572 0.01032 0.00341 -0.0056 0.5372 1.0000
0.250 0.1822 0.01043 0.00334 -0.0050 0.5313 1.0000
0.500 0.2075 0.01050 0.00335 -0.0046 0.5244 1.0000
0.750 0.2326 0.01061 0.00333 -0.0040 0.5186 1.0000
1.000 0.2580 0.01073 0.00338 -0.0036 0.5127 1.0000
1.250 0.2833 0.01084 0.00342 -0.0031 0.5069 1.0000
1.500 0.3086 0.01100 0.00348 -0.0026 0.5017 1.0000
1.750 0.3341 0.01111 0.00359 -0.0022 0.4953 1.0000
2.000 0.3593 0.01128 0.00367 -0.0017 0.4905 1.0000
2.250 0.3849 0.01144 0.00385 -0.0013 0.4849 1.0000
2.500 0.4102 0.01160 0.00398 -0.0009 0.4794 1.0000
2.750 0.4355 0.01180 0.00413 -0.0004 0.4746 1.0000
3.000 0.4611 0.01197 0.00435 0.0000 0.4686 1.0000
3.250 0.4865 0.01217 0.00455 0.0005 0.4640 1.0000
3.500 0.5120 0.01239 0.00482 0.0008 0.4588 1.0000
3.750 0.5374 0.01259 0.00506 0.0012 0.4530 1.0000
4.000 0.5628 0.01283 0.00527 0.0017 0.4488 1.0000
4.250 0.5883 0.01308 0.00565 0.0020 0.4431 1.0000
4.500 0.6138 0.01330 0.00596 0.0025 0.4379 1.0000
4.750 0.6392 0.01359 0.00627 0.0029 0.4336 1.0000
5.000 0.6647 0.01386 0.00671 0.0032 0.4276 1.0000
5.250 0.6901 0.01410 0.00700 0.0037 0.4228 1.0000
5.500 0.7154 0.01440 0.00745 0.0041 0.4172 1.0000
5.750 0.7404 0.01426 0.00734 0.0049 0.4064 1.0000
6.000 0.7648 0.01379 0.00699 0.0057 0.3877 1.0000
6.250 0.7894 0.01331 0.00651 0.0066 0.3667 1.0000
6.500 0.8142 0.01293 0.00629 0.0073 0.3328 1.0000
6.750 0.8300 0.01459 0.00693 0.0079 0.1182 1.0000
7.000 0.8446 0.01721 0.00913 0.0087 0.0437 1.0000
7.250 0.8635 0.01864 0.01077 0.0096 0.0357 1.0000
7.500 0.8805 0.02018 0.01244 0.0105 0.0315 1.0000
7.750 0.8907 0.02264 0.01494 0.0123 0.0284 1.0000
8.000 0.9099 0.02366 0.01608 0.0133 0.0253 1.0000
8.250 0.9259 0.02534 0.01784 0.0148 0.0238 1.0000
8.500 0.9427 0.02722 0.01980 0.0164 0.0226 1.0000
8.750 0.9606 0.02938 0.02209 0.0179 0.0221 1.0000
9.000 0.9797 0.03201 0.02492 0.0193 0.0223 1.0000
9.250 0.9972 0.03533 0.02860 0.0209 0.0235 1.0000
9.500 1.0108 0.03856 0.03218 0.0222 0.0239 1.0000
9.750 1.0232 0.04042 0.03413 0.0228 0.0211 1.0000
10.000 1.0274 0.04446 0.03872 0.0245 0.0225 1.0000
10.250 1.0250 0.04978 0.04448 0.0259 0.0256 1.0000
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