FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 50,000 Max Cl/Cd: 32.13 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h80-il-50000.txt Download as CSV file: xf-fx66h80-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4726 0.09436 0.08922 0.0178 1.0000 0.2123
-7.500 -0.4638 0.08975 0.08467 0.0182 1.0000 0.2257
-7.250 -0.5611 0.09595 0.09049 0.0191 1.0000 0.2121
-7.000 -0.5554 0.09208 0.08668 0.0185 1.0000 0.2259
-6.750 -0.5458 0.08769 0.08237 0.0191 1.0000 0.2410
-6.500 -0.5293 0.08336 0.07809 0.0217 1.0000 0.2615
-6.250 -0.5366 0.08087 0.07567 0.0184 1.0000 0.2818
-6.000 -0.5287 0.07737 0.07224 0.0197 1.0000 0.3092
-5.750 -0.5086 0.07297 0.06789 0.0251 1.0000 0.3451
-5.500 -0.5014 0.06997 0.06499 0.0284 1.0000 0.3897
-4.750 -0.2120 0.04983 0.04433 0.0366 1.0000 0.9226
-4.500 -0.2742 0.05147 0.04624 0.0459 1.0000 0.8368
-4.250 -0.3262 0.05152 0.04657 0.0501 1.0000 0.7654
-4.000 -0.3200 0.03376 0.02991 0.0340 1.0000 0.6290
-3.750 -0.3342 0.03958 0.03262 -0.0087 1.0000 0.1670
-3.500 -0.3069 0.03631 0.02886 -0.0094 1.0000 0.1370
-3.250 -0.3098 0.03566 0.02786 -0.0070 1.0000 0.1280
-3.000 -0.2493 0.03180 0.02345 -0.0139 0.9709 0.1227
-2.750 -0.1828 0.02884 0.01942 -0.0196 0.9451 0.1154
-2.500 -0.1252 0.02597 0.01606 -0.0241 0.9203 0.1165
-2.250 -0.0757 0.02394 0.01388 -0.0271 0.8963 0.1337
-2.000 0.0570 0.01677 0.00945 -0.0410 0.8813 1.0000
-1.750 0.0811 0.01720 0.00914 -0.0399 0.8563 1.0000
-1.500 0.1030 0.01765 0.00912 -0.0387 0.8352 1.0000
-1.250 0.1248 0.01810 0.00918 -0.0376 0.8174 1.0000
-1.000 0.1476 0.01856 0.00932 -0.0368 0.8009 1.0000
-0.750 0.1704 0.01904 0.00953 -0.0361 0.7861 1.0000
-0.500 0.1935 0.01953 0.00975 -0.0354 0.7727 1.0000
-0.250 0.2166 0.02005 0.01005 -0.0348 0.7601 1.0000
0.000 0.2393 0.02059 0.01040 -0.0340 0.7485 1.0000
0.250 0.2625 0.02115 0.01080 -0.0335 0.7375 1.0000
0.500 0.2867 0.02178 0.01131 -0.0334 0.7263 1.0000
0.750 0.3104 0.02244 0.01187 -0.0332 0.7161 1.0000
1.000 0.3332 0.02311 0.01242 -0.0326 0.7070 1.0000
1.250 0.3565 0.02382 0.01306 -0.0323 0.6974 1.0000
1.500 0.3805 0.02466 0.01387 -0.0326 0.6881 1.0000
1.750 0.4030 0.02543 0.01458 -0.0320 0.6800 1.0000
2.000 0.4264 0.02634 0.01552 -0.0321 0.6711 1.0000
2.250 0.4494 0.02736 0.01655 -0.0324 0.6629 1.0000
2.500 0.4714 0.02823 0.01741 -0.0317 0.6554 1.0000
2.750 0.4939 0.02952 0.01878 -0.0326 0.6470 1.0000
3.000 0.5156 0.03042 0.01968 -0.0316 0.6407 1.0000
3.250 0.5364 0.03202 0.02146 -0.0329 0.6324 1.0000
3.500 0.5576 0.03310 0.02257 -0.0322 0.6261 1.0000
3.750 0.5758 0.03497 0.02458 -0.0335 0.6185 1.0000
4.000 0.5967 0.03614 0.02580 -0.0326 0.6125 1.0000
4.250 0.6108 0.03843 0.02825 -0.0342 0.6054 1.0000
4.500 0.6318 0.03967 0.02958 -0.0332 0.5997 1.0000
4.750 0.6397 0.04248 0.03260 -0.0349 0.5934 1.0000
5.000 0.6560 0.04432 0.03456 -0.0348 0.5878 1.0000
5.250 0.6642 0.04688 0.03724 -0.0353 0.5824 1.0000
5.500 0.6679 0.04970 0.04015 -0.0360 0.5780 1.0000
5.750 0.6894 0.05132 0.04193 -0.0352 0.5713 1.0000
6.000 0.6819 0.05481 0.04546 -0.0360 0.5687 1.0000
6.250 0.6773 0.05793 0.04862 -0.0362 0.5670 1.0000
6.500 0.6715 0.06089 0.05161 -0.0356 0.5668 1.0000
6.750 0.6684 0.06392 0.05469 -0.0354 0.5680 1.0000
7.000 0.6718 0.06721 0.05809 -0.0361 0.5730 1.0000
7.250 0.6902 0.06938 0.06045 -0.0354 0.5579 1.0000
7.500 0.8965 0.02790 0.02046 0.0081 0.3166 1.0000
7.750 0.8938 0.03030 0.02102 0.0110 0.1473 1.0000
8.000 0.8963 0.03354 0.02389 0.0122 0.1212 1.0000
8.250 0.9031 0.03610 0.02633 0.0140 0.1064 1.0000
8.500 0.9188 0.03827 0.02842 0.0166 0.0973 1.0000
8.750 0.9463 0.04063 0.03065 0.0192 0.0893 1.0000
9.000 0.9673 0.04337 0.03371 0.0207 0.0826 1.0000
9.250 0.9909 0.04669 0.03706 0.0218 0.0773 1.0000
9.500 1.0119 0.05091 0.04153 0.0228 0.0763 1.0000
9.750 1.0242 0.05493 0.04602 0.0237 0.0765 1.0000
10.000 1.0269 0.05870 0.05034 0.0246 0.0775 1.0000
10.250 1.0161 0.06281 0.05503 0.0249 0.0790 1.0000
10.500 0.9996 0.06721 0.05982 0.0245 0.0804 1.0000
10.750 0.9775 0.07154 0.06437 0.0236 0.0814 1.0000
11.000 0.9527 0.07680 0.06978 0.0207 0.0823 1.0000
11.250 0.9279 0.08302 0.07611 0.0163 0.0835 1.0000
11.500 0.9038 0.09022 0.08337 0.0113 0.0849 1.0000
11.750 0.8840 0.09784 0.09099 0.0066 0.0865 1.0000
12.000 0.8802 0.10391 0.09707 0.0047 0.0880 1.0000
12.250 0.8178 0.12209 0.11509 -0.0107 0.0978 1.0000
12.500 0.8157 0.12836 0.12133 -0.0129 0.0997 1.0000
12.750 0.7989 0.13890 0.13176 -0.0192 0.1118 1.0000
13.000 0.8096 0.14384 0.13675 -0.0192 0.1141 1.0000
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Polar data table (+)
Polar graphs
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