FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 500,000 Max Cl/Cd: 69.84 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h60-il-500000.txt Download as CSV file: xf-fx66h60-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5227 0.08549 0.08354 0.0252 1.0000 0.0099
-7.750 -0.5243 0.08119 0.07927 0.0236 1.0000 0.0100
-7.500 -0.5275 0.07692 0.07502 0.0218 1.0000 0.0100
-7.250 -0.5339 0.07267 0.07080 0.0196 1.0000 0.0101
-7.000 -0.5431 0.06858 0.06671 0.0174 1.0000 0.0100
-6.750 -0.5440 0.06389 0.06200 0.0150 1.0000 0.0102
-6.500 -0.5415 0.05907 0.05714 0.0129 1.0000 0.0103
-6.250 -0.5359 0.05426 0.05228 0.0111 1.0000 0.0105
-6.000 -0.5275 0.04946 0.04740 0.0097 1.0000 0.0108
-5.750 -0.5165 0.04480 0.04264 0.0086 1.0000 0.0112
-5.500 -0.5026 0.04030 0.03803 0.0078 1.0000 0.0118
-5.250 -0.4849 0.03628 0.03387 0.0074 1.0000 0.0125
-5.000 -0.4617 0.03360 0.03103 0.0076 1.0000 0.0133
-4.750 -0.4412 0.03047 0.02774 0.0080 1.0000 0.0136
-4.500 -0.4221 0.02702 0.02412 0.0085 1.0000 0.0137
-4.250 -0.4025 0.02360 0.02050 0.0092 1.0000 0.0138
-4.000 -0.3825 0.02040 0.01708 0.0101 1.0000 0.0138
-2.000 -0.1864 0.01409 0.00774 0.0146 0.7160 0.0217
-1.750 -0.1612 0.01215 0.00539 0.0161 0.6654 0.0175
-1.500 -0.1368 0.01109 0.00405 0.0174 0.6223 0.0163
-1.250 -0.1125 0.01040 0.00312 0.0185 0.5853 0.0166
-1.000 -0.0876 0.00996 0.00250 0.0193 0.5519 0.0192
-0.750 -0.0619 0.00969 0.00206 0.0200 0.5224 0.0229
-0.500 -0.0363 0.00932 0.00157 0.0207 0.4973 0.0426
-0.250 -0.0373 0.00634 0.00146 0.0263 0.4821 0.8872
0.000 -0.0105 0.00654 0.00165 0.0280 0.4603 0.9591
0.250 0.0932 0.00720 0.00193 0.0125 0.4240 0.9878
0.500 0.1639 0.00729 0.00179 0.0032 0.4002 0.9997
0.750 0.1896 0.00732 0.00172 0.0036 0.3861 1.0000
1.000 0.2134 0.00737 0.00167 0.0043 0.3731 1.0000
1.250 0.2373 0.00742 0.00164 0.0051 0.3617 1.0000
1.500 0.2613 0.00747 0.00162 0.0058 0.3511 1.0000
1.750 0.2853 0.00752 0.00163 0.0065 0.3414 1.0000
2.000 0.3093 0.00759 0.00164 0.0072 0.3322 1.0000
2.250 0.3332 0.00765 0.00168 0.0079 0.3233 1.0000
2.500 0.3573 0.00771 0.00172 0.0087 0.3150 1.0000
2.750 0.3813 0.00782 0.00178 0.0094 0.3075 1.0000
3.000 0.4054 0.00788 0.00185 0.0101 0.3002 1.0000
3.250 0.4291 0.00800 0.00194 0.0109 0.2936 1.0000
3.500 0.4531 0.00808 0.00204 0.0116 0.2866 1.0000
3.750 0.4765 0.00823 0.00220 0.0124 0.2804 1.0000
4.000 0.5003 0.00831 0.00235 0.0132 0.2745 1.0000
4.250 0.5237 0.00848 0.00251 0.0141 0.2690 1.0000
4.500 0.5472 0.00858 0.00268 0.0149 0.2625 1.0000
4.750 0.5706 0.00865 0.00276 0.0157 0.2500 1.0000
5.000 0.5941 0.00874 0.00291 0.0166 0.2373 1.0000
5.250 0.6174 0.00884 0.00299 0.0174 0.2162 1.0000
5.500 0.6398 0.00919 0.00316 0.0182 0.1618 1.0000
5.750 0.6545 0.01148 0.00480 0.0199 0.0150 1.0000
6.000 0.6768 0.01215 0.00563 0.0210 0.0122 1.0000
6.250 0.6985 0.01303 0.00667 0.0221 0.0109 1.0000
6.500 0.7195 0.01411 0.00791 0.0233 0.0104 1.0000
6.750 0.7398 0.01539 0.00935 0.0246 0.0103 1.0000
7.000 0.7600 0.01681 0.01096 0.0258 0.0104 1.0000
7.250 0.7806 0.01804 0.01226 0.0266 0.0093 1.0000
7.500 0.7978 0.02047 0.01483 0.0278 0.0084 1.0000
7.750 0.8154 0.02348 0.01806 0.0291 0.0082 1.0000
8.000 0.8318 0.02710 0.02198 0.0302 0.0081 1.0000
8.250 0.8533 0.02846 0.02352 0.0310 0.0084 1.0000
10.750 0.7076 0.07417 0.07183 0.0125 0.0151 1.0000
11.000 0.6921 0.08165 0.07937 0.0082 0.0151 1.0000
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Polar data table (+)
Polar graphs
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