FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.81 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h60-il-1000000-n5.txt Download as CSV file: xf-fx66h60-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6289 0.08716 0.08569 0.0250 1.0000 0.0019
-7.750 -0.6304 0.08422 0.08277 0.0226 1.0000 0.0019
-7.500 -0.6290 0.08006 0.07860 0.0196 1.0000 0.0020
-7.250 -0.6224 0.07660 0.07512 0.0172 1.0000 0.0021
-7.000 -0.6148 0.07276 0.07125 0.0149 1.0000 0.0022
-6.750 -0.6060 0.06860 0.06704 0.0128 1.0000 0.0024
-6.500 -0.5955 0.06429 0.06267 0.0110 1.0000 0.0025
-6.250 -0.5825 0.06027 0.05858 0.0097 1.0000 0.0028
-6.000 -0.5685 0.05593 0.05414 0.0087 1.0000 0.0028
-5.750 -0.5527 0.05174 0.04984 0.0081 1.0000 0.0030
-5.500 -0.5156 0.04642 0.04395 0.0033 0.8189 0.0034
-5.250 -0.4994 0.04300 0.04013 0.0044 0.7415 0.0037
-5.000 -0.4811 0.03946 0.03627 0.0053 0.6939 0.0038
-4.500 -0.4425 0.03156 0.02769 0.0077 0.6218 0.0036
-4.000 -0.3942 0.01070 0.00630 0.0117 0.5516 0.0037
-3.500 -0.3523 0.01671 0.01114 0.0144 0.5224 0.0054
-3.250 -0.3267 0.01610 0.01033 0.0148 0.4981 0.0059
-3.000 -0.3009 0.01501 0.00897 0.0154 0.4763 0.0063
-2.750 -0.2747 0.01414 0.00790 0.0159 0.4577 0.0069
-2.500 -0.2483 0.01328 0.00687 0.0164 0.4410 0.0074
-2.250 -0.2222 0.01200 0.00536 0.0172 0.4247 0.0071
-2.000 -0.1964 0.01097 0.00417 0.0180 0.4093 0.0069
-1.750 -0.1710 0.01019 0.00324 0.0187 0.3958 0.0067
-1.500 -0.1455 0.00960 0.00252 0.0194 0.3836 0.0065
-1.250 -0.1196 0.00918 0.00197 0.0200 0.3710 0.0064
-1.000 -0.0932 0.00891 0.00155 0.0204 0.3591 0.0064
-0.750 -0.0664 0.00872 0.00126 0.0208 0.3487 0.0065
-0.500 -0.0394 0.00860 0.00105 0.0211 0.3392 0.0068
-0.250 -0.0122 0.00852 0.00090 0.0213 0.3299 0.0077
0.000 0.0149 0.00845 0.00082 0.0215 0.3207 0.0148
0.250 0.0415 0.00829 0.00076 0.0218 0.3116 0.0614
0.750 0.0707 0.00566 0.00072 0.0269 0.2992 0.9072
1.000 0.0947 0.00568 0.00077 0.0281 0.2927 0.9328
1.250 0.1189 0.00573 0.00081 0.0292 0.2854 0.9507
1.500 0.1459 0.00579 0.00082 0.0295 0.2781 0.9562
1.750 0.1744 0.00585 0.00083 0.0294 0.2715 0.9581
2.000 0.2029 0.00591 0.00085 0.0293 0.2656 0.9601
2.250 0.2312 0.00598 0.00088 0.0292 0.2596 0.9625
2.500 0.2593 0.00604 0.00092 0.0292 0.2546 0.9650
2.750 0.2872 0.00612 0.00098 0.0292 0.2483 0.9676
3.000 0.3164 0.00619 0.00104 0.0288 0.2428 0.9694
3.250 0.3462 0.00627 0.00111 0.0284 0.2376 0.9711
3.500 0.3760 0.00637 0.00119 0.0279 0.2326 0.9729
3.750 0.4059 0.00645 0.00128 0.0274 0.2285 0.9750
4.000 0.4356 0.00655 0.00138 0.0270 0.2231 0.9772
4.250 0.4648 0.00666 0.00152 0.0266 0.2184 0.9796
4.500 0.4940 0.00676 0.00164 0.0262 0.2108 0.9818
4.750 0.5244 0.00697 0.00177 0.0255 0.1894 0.9832
5.000 0.5546 0.00722 0.00194 0.0248 0.1666 0.9848
5.250 0.5820 0.00824 0.00249 0.0241 0.0653 0.9871
5.500 0.6103 0.00901 0.00304 0.0235 0.0145 0.9894
5.750 0.6397 0.00933 0.00343 0.0230 0.0084 0.9918
6.000 0.6685 0.00976 0.00390 0.0226 0.0049 0.9943
6.250 0.6983 0.01007 0.00424 0.0219 0.0036 0.9967
6.500 0.7278 0.01046 0.00469 0.0213 0.0028 0.9990
6.750 0.7542 0.01092 0.00522 0.0213 0.0024 1.0000
7.000 0.7767 0.01148 0.00587 0.0222 0.0020 1.0000
7.250 0.7976 0.01251 0.00709 0.0233 0.0017 1.0000
7.500 0.8210 0.01298 0.00767 0.0239 0.0016 1.0000
7.750 0.8445 0.01348 0.00824 0.0244 0.0015 1.0000
8.000 0.8673 0.01420 0.00908 0.0250 0.0013 1.0000
8.250 0.8888 0.01521 0.01024 0.0257 0.0011 1.0000
8.500 0.9090 0.01651 0.01172 0.0266 0.0011 1.0000
8.750 0.9278 0.01810 0.01351 0.0274 0.0010 1.0000
9.000 0.9449 0.02003 0.01567 0.0284 0.0010 1.0000
9.250 0.9598 0.02238 0.01829 0.0295 0.0009 1.0000
9.500 0.9720 0.02518 0.02139 0.0305 0.0009 1.0000
9.750 0.9789 0.02882 0.02539 0.0316 0.0009 1.0000
10.000 0.9800 0.03295 0.02988 0.0325 0.0010 1.0000
10.250 0.9748 0.03722 0.03446 0.0329 0.0010 1.0000
10.500 0.9579 0.04145 0.03893 0.0331 0.0010 1.0000
10.750 0.9429 0.04650 0.04413 0.0284 0.0010 1.0000
11.000 0.9307 0.05267 0.05045 0.0227 0.0010 1.0000
11.250 0.9195 0.05893 0.05683 0.0175 0.0010 1.0000
11.500 0.9043 0.06601 0.06402 0.0122 0.0010 1.0000
11.750 0.8886 0.07332 0.07142 0.0072 0.0010 1.0000
12.000 0.8754 0.08020 0.07837 0.0027 0.0010 1.0000
12.250 0.8653 0.08658 0.08481 -0.0012 0.0010 1.0000
12.500 0.8497 0.09446 0.09274 -0.0057 0.0010 1.0000
12.750 0.8353 0.10267 0.10101 -0.0102 0.0010 1.0000
13.000 0.8139 0.11366 0.11206 -0.0154 0.0011 1.0000
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