S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Reynolds number: 50,000 Max Cl/Cd: 32.58 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8066-il-50000.txt Download as CSV file: xf-s8066-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4945 0.09847 0.09166 -0.0077 1.0000 0.3267
-8.500 -0.5025 0.09592 0.08921 -0.0077 1.0000 0.3396
-8.250 -0.4804 0.09088 0.08412 -0.0071 1.0000 0.3484
-8.000 -0.6029 0.07056 0.06401 -0.0374 1.0000 0.1347
-7.750 -0.6199 0.06482 0.05807 -0.0381 1.0000 0.1212
-7.500 -0.6383 0.05969 0.05247 -0.0371 1.0000 0.1108
-7.250 -0.6365 0.05575 0.04838 -0.0353 1.0000 0.1088
-7.000 -0.6356 0.05196 0.04433 -0.0332 1.0000 0.1065
-6.750 -0.6335 0.04840 0.04041 -0.0309 1.0000 0.1058
-6.500 -0.6282 0.04498 0.03656 -0.0284 1.0000 0.1051
-6.250 -0.6192 0.04176 0.03289 -0.0261 1.0000 0.1052
-6.000 -0.6068 0.03860 0.02926 -0.0238 1.0000 0.1059
-5.750 -0.5912 0.03576 0.02593 -0.0217 1.0000 0.1083
-5.500 -0.5743 0.03321 0.02305 -0.0198 1.0000 0.1165
-5.250 -0.5549 0.03084 0.02028 -0.0179 1.0000 0.1281
-5.000 -0.5349 0.02874 0.01820 -0.0163 1.0000 0.1479
-4.750 -0.5140 0.02668 0.01616 -0.0146 1.0000 0.1764
-4.500 -0.4927 0.02465 0.01434 -0.0129 1.0000 0.2186
-4.250 -0.4737 0.02253 0.01273 -0.0109 1.0000 0.2909
-4.000 -0.4667 0.01990 0.01175 -0.0065 1.0000 0.4783
-3.750 -0.4688 0.01984 0.01282 0.0040 1.0000 0.7051
-3.500 -0.4625 0.02067 0.01356 0.0125 1.0000 0.8004
-3.250 -0.4191 0.02216 0.01464 0.0160 1.0000 0.8837
-3.000 -0.0995 0.02282 0.01321 -0.0322 1.0000 0.9922
-2.750 -0.0729 0.02206 0.01225 -0.0346 1.0000 1.0000
-2.500 -0.0745 0.02169 0.01182 -0.0316 1.0000 1.0000
-2.250 -0.0772 0.02136 0.01143 -0.0283 1.0000 1.0000
-2.000 -0.0803 0.02107 0.01108 -0.0248 1.0000 1.0000
-1.750 -0.0836 0.02081 0.01076 -0.0212 1.0000 1.0000
-1.500 -0.0869 0.02057 0.01045 -0.0175 1.0000 1.0000
-1.250 -0.0901 0.02034 0.01015 -0.0137 1.0000 1.0000
-1.000 -0.0929 0.02014 0.00988 -0.0099 1.0000 1.0000
-0.750 -0.0946 0.01996 0.00963 -0.0061 1.0000 1.0000
-0.500 -0.0937 0.01984 0.00943 -0.0028 1.0000 1.0000
-0.250 -0.0895 0.01979 0.00928 0.0001 1.0000 1.0000
0.000 -0.0814 0.01982 0.00921 0.0023 1.0000 1.0000
0.250 -0.0700 0.01995 0.00923 0.0040 1.0000 1.0000
0.500 -0.0564 0.02014 0.00932 0.0054 1.0000 1.0000
0.750 -0.0414 0.02040 0.00950 0.0064 1.0000 1.0000
1.000 -0.0255 0.02070 0.00974 0.0073 1.0000 1.0000
1.250 -0.0090 0.02106 0.01004 0.0081 1.0000 1.0000
1.500 0.0079 0.02147 0.01041 0.0087 1.0000 1.0000
1.750 0.0249 0.02192 0.01084 0.0092 1.0000 1.0000
2.000 0.0420 0.02242 0.01133 0.0097 1.0000 1.0000
2.250 0.0591 0.02297 0.01188 0.0101 1.0000 1.0000
2.500 0.0761 0.02357 0.01250 0.0103 1.0000 1.0000
2.750 0.0930 0.02423 0.01321 0.0106 1.0000 1.0000
3.000 0.1097 0.02495 0.01396 0.0107 1.0000 1.0000
3.250 0.1521 0.02637 0.01550 0.0058 0.9875 1.0000
3.500 0.2085 0.02807 0.01739 -0.0014 0.9660 1.0000
3.750 0.2682 0.02969 0.01928 -0.0088 0.9424 1.0000
4.000 0.3195 0.03083 0.02068 -0.0141 0.9158 1.0000
4.250 0.3784 0.03174 0.02196 -0.0198 0.8863 1.0000
4.500 0.4302 0.03209 0.02266 -0.0235 0.8525 1.0000
4.750 0.5061 0.03120 0.02237 -0.0286 0.8106 1.0000
5.000 0.6053 0.02718 0.01918 -0.0322 0.7563 1.0000
5.250 0.6577 0.02350 0.01605 -0.0282 0.6925 1.0000
5.500 0.6855 0.02104 0.01331 -0.0204 0.5381 1.0000
5.750 0.6861 0.02317 0.01359 -0.0134 0.3374 1.0000
6.000 0.7036 0.02567 0.01528 -0.0113 0.2552 1.0000
6.250 0.7298 0.02780 0.01711 -0.0106 0.2096 1.0000
6.500 0.7612 0.03020 0.01947 -0.0104 0.1825 1.0000
6.750 0.7883 0.03262 0.02173 -0.0100 0.1607 1.0000
7.000 0.8152 0.03550 0.02478 -0.0094 0.1473 1.0000
7.250 0.8360 0.03817 0.02767 -0.0081 0.1337 1.0000
7.500 0.8516 0.04126 0.03148 -0.0059 0.1272 1.0000
7.750 0.8689 0.04450 0.03484 -0.0046 0.1181 1.0000
8.000 0.8784 0.04820 0.03919 -0.0022 0.1158 1.0000
8.250 0.8838 0.05208 0.04361 0.0001 0.1136 1.0000
8.500 0.8876 0.05589 0.04788 0.0022 0.1113 1.0000
8.750 0.8874 0.06002 0.05238 0.0042 0.1104 1.0000
9.000 0.8772 0.06476 0.05753 0.0062 0.1127 1.0000
9.250 0.8670 0.06961 0.06264 0.0076 0.1155 1.0000
9.500 0.8666 0.07479 0.06791 0.0083 0.1185 1.0000
9.750 0.8196 0.07946 0.07282 0.0092 0.1244 1.0000
10.000 0.7952 0.08552 0.07891 0.0077 0.1304 1.0000
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Polar data table (+)
Polar graphs
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