FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 200,000 Max Cl/Cd: 51.31 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h60-il-200000-n5.txt Download as CSV file: xf-fx66h60-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-60
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5263 0.08690 0.08391 0.0194 1.0000 0.0183
-7.500 -0.5302 0.08268 0.07972 0.0168 1.0000 0.0184
-7.250 -0.5343 0.07864 0.07567 0.0150 1.0000 0.0184
-7.000 -0.5335 0.07419 0.07120 0.0131 1.0000 0.0184
-6.750 -0.5304 0.06961 0.06657 0.0116 1.0000 0.0184
-6.500 -0.5252 0.06499 0.06189 0.0103 1.0000 0.0185
-6.250 -0.5180 0.06030 0.05712 0.0093 1.0000 0.0185
-6.000 -0.5089 0.05561 0.05233 0.0085 1.0000 0.0185
-5.750 -0.4982 0.05099 0.04760 0.0081 1.0000 0.0186
-5.500 -0.4858 0.04645 0.04291 0.0078 1.0000 0.0186
-5.250 -0.4719 0.04196 0.03827 0.0077 1.0000 0.0186
-5.000 -0.4569 0.03758 0.03372 0.0079 1.0000 0.0186
-4.750 -0.4407 0.03332 0.02928 0.0082 1.0000 0.0186
-4.500 -0.4552 0.04011 0.03561 0.0092 1.0000 0.0160
-4.250 -0.4347 0.03623 0.03147 0.0099 1.0000 0.0141
-4.000 -0.4119 0.03249 0.02741 0.0110 1.0000 0.0132
-3.750 -0.3880 0.02911 0.02368 0.0123 1.0000 0.0129
-3.500 -0.3631 0.02682 0.02111 0.0133 1.0000 0.0153
-3.250 -0.3372 0.02456 0.01845 0.0144 1.0000 0.0167
-3.000 -0.3121 0.02199 0.01553 0.0155 1.0000 0.0160
-2.750 -0.2860 0.01978 0.01301 0.0165 1.0000 0.0154
-2.500 -0.2349 0.01742 0.01000 0.0126 0.8222 0.0147
-2.250 -0.2077 0.01619 0.00828 0.0136 0.7428 0.0145
-2.000 -0.1827 0.01517 0.00687 0.0148 0.6873 0.0144
-1.750 -0.1582 0.01428 0.00570 0.0160 0.6420 0.0145
-1.500 -0.1340 0.01353 0.00472 0.0171 0.6041 0.0149
-1.250 -0.1097 0.01294 0.00385 0.0181 0.5712 0.0158
-1.000 -0.0849 0.01253 0.00320 0.0189 0.5425 0.0174
-0.750 -0.0597 0.01213 0.00260 0.0197 0.5170 0.0236
-0.500 -0.0365 0.01140 0.00225 0.0204 0.4949 0.1502
-0.250 0.0672 0.00955 0.00263 0.0067 0.4567 0.9950
0.000 0.1045 0.00958 0.00238 0.0046 0.4362 1.0000
0.250 0.1283 0.00962 0.00226 0.0053 0.4209 1.0000
0.500 0.1521 0.00967 0.00216 0.0061 0.4065 1.0000
0.750 0.1760 0.00973 0.00209 0.0068 0.3931 1.0000
1.000 0.2000 0.00979 0.00204 0.0075 0.3806 1.0000
1.250 0.2240 0.00985 0.00202 0.0082 0.3696 1.0000
1.500 0.2480 0.00993 0.00201 0.0089 0.3592 1.0000
1.750 0.2719 0.01003 0.00203 0.0097 0.3492 1.0000
2.000 0.2958 0.01013 0.00207 0.0104 0.3399 1.0000
2.250 0.3197 0.01023 0.00214 0.0111 0.3311 1.0000
2.500 0.3436 0.01035 0.00226 0.0119 0.3235 1.0000
2.750 0.3674 0.01047 0.00236 0.0126 0.3154 1.0000
3.000 0.3913 0.01061 0.00249 0.0134 0.3079 1.0000
3.250 0.4151 0.01076 0.00263 0.0141 0.3009 1.0000
3.500 0.4390 0.01091 0.00281 0.0149 0.2944 1.0000
3.750 0.4628 0.01108 0.00300 0.0156 0.2883 1.0000
4.000 0.4867 0.01126 0.00329 0.0164 0.2821 1.0000
4.250 0.5106 0.01145 0.00352 0.0171 0.2758 1.0000
4.500 0.5345 0.01167 0.00379 0.0178 0.2706 1.0000
4.750 0.5587 0.01187 0.00411 0.0185 0.2650 1.0000
5.000 0.5827 0.01212 0.00441 0.0193 0.2597 1.0000
5.250 0.6070 0.01227 0.00467 0.0199 0.2478 1.0000
5.500 0.6311 0.01235 0.00478 0.0205 0.2206 1.0000
5.750 0.6542 0.01275 0.00509 0.0211 0.1510 1.0000
6.000 0.6711 0.01495 0.00657 0.0220 0.0230 1.0000
6.250 0.6936 0.01592 0.00776 0.0228 0.0157 1.0000
6.500 0.7159 0.01690 0.00893 0.0235 0.0116 1.0000
6.750 0.7343 0.01879 0.01114 0.0245 0.0098 1.0000
7.000 0.7541 0.02024 0.01274 0.0255 0.0093 1.0000
7.250 0.7737 0.02181 0.01445 0.0265 0.0089 1.0000
7.500 0.7930 0.02358 0.01639 0.0275 0.0086 1.0000
7.750 0.8122 0.02554 0.01853 0.0285 0.0082 1.0000
8.000 0.8322 0.02708 0.02037 0.0292 0.0073 1.0000
8.250 0.8523 0.02799 0.02144 0.0294 0.0056 1.0000
8.500 0.8686 0.03010 0.02376 0.0300 0.0052 1.0000
8.750 0.8817 0.03294 0.02689 0.0306 0.0049 1.0000
9.000 0.8898 0.03666 0.03097 0.0311 0.0047 1.0000
9.250 0.8930 0.04077 0.03547 0.0313 0.0046 1.0000
9.500 0.8923 0.04472 0.03976 0.0312 0.0045 1.0000
9.750 0.8855 0.04875 0.04409 0.0304 0.0045 1.0000
10.000 0.8753 0.05226 0.04778 0.0288 0.0045 1.0000
10.250 0.8686 0.05633 0.05200 0.0252 0.0046 1.0000
10.500 0.8533 0.06270 0.05854 0.0198 0.0045 1.0000
10.750 0.8459 0.06800 0.06395 0.0154 0.0046 1.0000
11.000 0.8355 0.07412 0.07018 0.0107 0.0046 1.0000
11.250 0.8290 0.07966 0.07582 0.0066 0.0046 1.0000
11.500 0.8186 0.08628 0.08253 0.0021 0.0047 1.0000
11.750 0.8071 0.09342 0.08975 -0.0024 0.0047 1.0000
12.000 0.7970 0.10084 0.09725 -0.0069 0.0049 1.0000
12.250 0.7811 0.11081 0.10729 -0.0121 0.0052 1.0000
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Polar data table (+)
Polar graphs
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