FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 50,000 Max Cl/Cd: 31.93 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h80-il-50000-n5.txt Download as CSV file: xf-fx66h80-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5610 0.12051 0.11433 0.0281 1.0000 0.0856
-9.000 -0.5662 0.11808 0.11199 0.0240 1.0000 0.0873
-8.750 -0.5726 0.11552 0.10954 0.0195 1.0000 0.0879
-8.500 -0.5481 0.10909 0.10308 0.0238 1.0000 0.0943
-8.250 -0.5479 0.10589 0.09996 0.0212 1.0000 0.0987
-8.000 -0.5601 0.10354 0.09775 0.0154 1.0000 0.1012
-7.750 -0.5446 0.09833 0.09257 0.0174 1.0000 0.1060
-7.500 -0.5423 0.09490 0.08921 0.0156 1.0000 0.1108
-7.250 -0.5522 0.09245 0.08678 0.0080 1.0000 0.1151
-7.000 -0.5370 0.08723 0.08166 0.0103 1.0000 0.1193
-6.750 -0.5301 0.08357 0.07801 0.0085 1.0000 0.1252
-6.500 -0.5261 0.07965 0.07410 0.0051 1.0000 0.1316
-6.250 -0.5142 0.07569 0.07016 0.0047 1.0000 0.1364
-5.750 -0.4928 0.06804 0.06247 0.0012 1.0000 0.1511
-5.500 -0.4591 0.05904 0.05282 -0.0050 1.0000 0.0551
-5.250 -0.4374 0.05435 0.04756 -0.0065 1.0000 0.0468
-5.000 -0.4203 0.05040 0.04355 -0.0067 1.0000 0.0453
-4.750 -0.4010 0.04674 0.03968 -0.0069 1.0000 0.0439
-4.500 -0.3800 0.04324 0.03582 -0.0070 1.0000 0.0427
-4.250 -0.3574 0.03993 0.03219 -0.0069 1.0000 0.0417
-4.000 -0.3334 0.03684 0.02873 -0.0069 1.0000 0.0410
-3.750 -0.2962 0.03361 0.02493 -0.0090 0.9036 0.0406
-3.500 -0.2626 0.03121 0.02188 -0.0095 0.8516 0.0424
-3.250 -0.2352 0.02950 0.01950 -0.0085 0.8154 0.0455
-2.750 -0.1826 0.02617 0.01522 -0.0061 0.7635 0.0495
-2.500 -0.1545 0.02473 0.01344 -0.0053 0.7423 0.0526
-2.250 -0.1246 0.02365 0.01195 -0.0046 0.7241 0.0596
-2.000 -0.0961 0.02264 0.01071 -0.0043 0.7074 0.0723
-1.750 -0.0703 0.02167 0.00954 -0.0033 0.6927 0.0864
-1.500 0.0255 0.01711 0.00788 -0.0148 0.6752 1.0000
-1.250 0.0500 0.01724 0.00744 -0.0140 0.6622 1.0000
-1.000 0.0744 0.01738 0.00716 -0.0132 0.6504 1.0000
-0.750 0.0988 0.01754 0.00695 -0.0125 0.6396 1.0000
-0.500 0.1236 0.01771 0.00682 -0.0120 0.6287 1.0000
-0.250 0.1486 0.01790 0.00676 -0.0115 0.6185 1.0000
0.000 0.1734 0.01811 0.00669 -0.0110 0.6092 1.0000
0.250 0.1981 0.01833 0.00669 -0.0104 0.6004 1.0000
0.500 0.2234 0.01857 0.00679 -0.0100 0.5913 1.0000
0.750 0.2482 0.01882 0.00687 -0.0095 0.5834 1.0000
1.000 0.2732 0.01909 0.00703 -0.0091 0.5750 1.0000
1.250 0.2981 0.01939 0.00723 -0.0087 0.5673 1.0000
1.500 0.3226 0.01969 0.00743 -0.0081 0.5600 1.0000
1.750 0.3476 0.02004 0.00775 -0.0078 0.5522 1.0000
2.000 0.3720 0.02037 0.00803 -0.0072 0.5457 1.0000
2.250 0.3973 0.02077 0.00844 -0.0071 0.5380 1.0000
2.500 0.4219 0.02113 0.00875 -0.0065 0.5318 1.0000
2.750 0.4470 0.02160 0.00928 -0.0064 0.5245 1.0000
3.000 0.4714 0.02200 0.00968 -0.0058 0.5185 1.0000
3.250 0.4962 0.02252 0.01035 -0.0056 0.5114 1.0000
3.500 0.5205 0.02298 0.01086 -0.0051 0.5054 1.0000
3.750 0.5450 0.02356 0.01154 -0.0049 0.4989 1.0000
4.000 0.5693 0.02410 0.01218 -0.0045 0.4925 1.0000
4.250 0.5935 0.02469 0.01290 -0.0042 0.4866 1.0000
4.500 0.6176 0.02537 0.01383 -0.0040 0.4799 1.0000
4.750 0.6416 0.02591 0.01449 -0.0033 0.4747 1.0000
5.000 0.6652 0.02679 0.01563 -0.0034 0.4673 1.0000
5.250 0.6891 0.02732 0.01629 -0.0026 0.4624 1.0000
5.500 0.7119 0.02838 0.01769 -0.0028 0.4545 1.0000
5.750 0.7356 0.02899 0.01848 -0.0021 0.4492 1.0000
6.000 0.7576 0.03016 0.02010 -0.0022 0.4412 1.0000
6.250 0.7810 0.03078 0.02098 -0.0014 0.4356 1.0000
6.500 0.8019 0.03207 0.02267 -0.0015 0.4269 1.0000
6.750 0.8258 0.03250 0.02340 -0.0003 0.4211 1.0000
7.000 0.8469 0.03207 0.02332 0.0015 0.3996 1.0000
7.250 0.8698 0.02749 0.01878 0.0064 0.3295 1.0000
7.500 0.8812 0.02760 0.01799 0.0082 0.1491 1.0000
7.750 0.8795 0.03182 0.02146 0.0082 0.0837 1.0000
8.000 0.8818 0.03501 0.02460 0.0085 0.0688 1.0000
8.250 0.8827 0.03796 0.02756 0.0088 0.0602 1.0000
8.500 0.8826 0.04077 0.03044 0.0091 0.0536 1.0000
8.750 0.8802 0.04365 0.03336 0.0092 0.0504 1.0000
9.000 0.8804 0.04617 0.03603 0.0099 0.0478 1.0000
9.250 0.8833 0.04847 0.03846 0.0110 0.0453 1.0000
9.500 0.8895 0.05051 0.04056 0.0124 0.0430 1.0000
9.750 0.8996 0.05229 0.04229 0.0150 0.0399 1.0000
10.000 0.9116 0.05430 0.04460 0.0163 0.0366 1.0000
10.250 0.9242 0.05646 0.04703 0.0178 0.0338 1.0000
10.500 0.9399 0.05886 0.04971 0.0196 0.0324 1.0000
10.750 0.9483 0.06202 0.05322 0.0204 0.0315 1.0000
11.000 0.9506 0.06571 0.05716 0.0202 0.0309 1.0000
11.250 0.9481 0.06976 0.06145 0.0193 0.0307 1.0000
11.500 0.9416 0.07428 0.06620 0.0177 0.0306 1.0000
11.750 0.9318 0.07933 0.07147 0.0154 0.0306 1.0000
12.000 0.9196 0.08481 0.07715 0.0124 0.0308 1.0000
12.250 0.9048 0.09098 0.08350 0.0087 0.0310 1.0000
12.500 0.8874 0.09801 0.09068 0.0043 0.0314 1.0000
12.750 0.8681 0.10600 0.09881 -0.0008 0.0320 1.0000
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Polar data table (+)
Polar graphs
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