S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Reynolds number: 200,000 Max Cl/Cd: 54.1 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8066-il-200000-n5.txt Download as CSV file: xf-s8066-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5854 0.08886 0.08530 -0.0272 1.0000 0.0111
-10.500 -0.5972 0.08111 0.07760 -0.0317 1.0000 0.0109
-10.250 -0.6202 0.06806 0.06457 -0.0411 1.0000 0.0106
-10.000 -0.6447 0.05974 0.05612 -0.0477 1.0000 0.0104
-9.750 -0.6672 0.05443 0.05066 -0.0499 1.0000 0.0103
-9.500 -0.6906 0.05026 0.04632 -0.0488 1.0000 0.0102
-9.250 -0.7084 0.04619 0.04200 -0.0466 1.0000 0.0101
-9.000 -0.7207 0.04205 0.03753 -0.0440 1.0000 0.0099
-8.750 -0.7285 0.03844 0.03355 -0.0408 1.0000 0.0099
-8.500 -0.7340 0.03536 0.03011 -0.0370 1.0000 0.0098
-8.250 -0.7366 0.03280 0.02719 -0.0330 1.0000 0.0097
-8.000 -0.7332 0.03033 0.02434 -0.0298 0.9994 0.0097
-7.750 -0.7094 0.02753 0.02107 -0.0304 0.9949 0.0098
-7.500 -0.6848 0.02531 0.01849 -0.0307 0.9906 0.0100
-7.250 -0.6579 0.02344 0.01633 -0.0313 0.9870 0.0102
-7.000 -0.6291 0.02182 0.01448 -0.0321 0.9841 0.0105
-6.750 -0.6027 0.02048 0.01295 -0.0323 0.9801 0.0110
-6.500 -0.5749 0.01929 0.01160 -0.0328 0.9764 0.0115
-6.250 -0.5456 0.01818 0.01033 -0.0337 0.9734 0.0122
-6.000 -0.5145 0.01733 0.00941 -0.0349 0.9710 0.0136
-5.750 -0.4882 0.01671 0.00869 -0.0350 0.9661 0.0160
-5.500 -0.4602 0.01588 0.00778 -0.0354 0.9621 0.0184
-5.250 -0.4301 0.01510 0.00692 -0.0362 0.9590 0.0252
-5.000 -0.4012 0.01447 0.00630 -0.0368 0.9555 0.0418
-4.750 -0.3757 0.01393 0.00589 -0.0367 0.9503 0.0677
-4.500 -0.3478 0.01333 0.00550 -0.0373 0.9464 0.1090
-4.250 -0.3182 0.01277 0.00509 -0.0381 0.9434 0.1552
-4.000 -0.2952 0.01227 0.00478 -0.0375 0.9375 0.2096
-3.750 -0.2704 0.01162 0.00447 -0.0374 0.9328 0.2964
-3.500 -0.2447 0.01097 0.00422 -0.0374 0.9291 0.4014
-3.250 -0.2235 0.01056 0.00409 -0.0362 0.9229 0.4837
-3.000 -0.1984 0.01025 0.00398 -0.0356 0.9181 0.5509
-2.750 -0.1714 0.01000 0.00390 -0.0353 0.9146 0.6069
-2.500 -0.1487 0.00989 0.00392 -0.0340 0.9081 0.6524
-2.250 -0.1224 0.00981 0.00390 -0.0334 0.9034 0.6926
-2.000 -0.0954 0.00978 0.00388 -0.0329 0.8992 0.7240
-1.750 -0.0711 0.00977 0.00389 -0.0320 0.8928 0.7484
-1.500 -0.0444 0.00974 0.00385 -0.0314 0.8880 0.7709
-1.250 -0.0189 0.00973 0.00386 -0.0306 0.8825 0.7900
-1.000 0.0066 0.00972 0.00385 -0.0299 0.8763 0.8063
-0.750 0.0340 0.00968 0.00380 -0.0294 0.8718 0.8197
-0.500 0.0588 0.00968 0.00380 -0.0287 0.8645 0.8315
-0.250 0.0857 0.00964 0.00375 -0.0283 0.8590 0.8427
0.000 0.1116 0.00962 0.00374 -0.0276 0.8521 0.8530
0.250 0.1383 0.00959 0.00372 -0.0272 0.8455 0.8625
0.500 0.1646 0.00956 0.00370 -0.0267 0.8383 0.8725
0.750 0.1915 0.00952 0.00368 -0.0262 0.8306 0.8819
1.000 0.2184 0.00949 0.00368 -0.0258 0.8217 0.8907
1.250 0.2461 0.00943 0.00363 -0.0255 0.8132 0.9001
1.500 0.2743 0.00939 0.00363 -0.0254 0.8015 0.9086
1.750 0.3029 0.00935 0.00361 -0.0253 0.7886 0.9174
2.000 0.3322 0.00929 0.00359 -0.0254 0.7739 0.9264
2.250 0.3636 0.00924 0.00354 -0.0258 0.7567 0.9338
2.500 0.3937 0.00922 0.00351 -0.0261 0.7341 0.9429
2.750 0.4268 0.00923 0.00346 -0.0269 0.7054 0.9497
3.000 0.4577 0.00931 0.00346 -0.0273 0.6690 0.9582
3.250 0.4900 0.00948 0.00349 -0.0281 0.6227 0.9658
3.500 0.5207 0.00975 0.00357 -0.0287 0.5678 0.9745
3.750 0.5502 0.01017 0.00374 -0.0293 0.4964 0.9840
4.000 0.5798 0.01087 0.00399 -0.0303 0.3957 0.9929
4.250 0.6044 0.01170 0.00437 -0.0305 0.2966 1.0000
4.500 0.6176 0.01239 0.00472 -0.0282 0.2266 1.0000
4.750 0.6329 0.01304 0.00511 -0.0263 0.1714 1.0000
5.000 0.6501 0.01364 0.00552 -0.0247 0.1306 1.0000
5.250 0.6691 0.01417 0.00595 -0.0233 0.1047 1.0000
5.500 0.6886 0.01472 0.00642 -0.0220 0.0868 1.0000
5.750 0.7089 0.01526 0.00692 -0.0209 0.0734 1.0000
6.000 0.7297 0.01578 0.00747 -0.0198 0.0635 1.0000
6.250 0.7504 0.01633 0.00807 -0.0187 0.0560 1.0000
6.500 0.7708 0.01693 0.00865 -0.0176 0.0478 1.0000
6.750 0.7923 0.01742 0.00915 -0.0168 0.0393 1.0000
7.000 0.8134 0.01799 0.00981 -0.0158 0.0335 1.0000
7.250 0.8336 0.01866 0.01047 -0.0148 0.0276 1.0000
7.500 0.8539 0.01935 0.01125 -0.0137 0.0232 1.0000
7.750 0.8717 0.02034 0.01228 -0.0123 0.0200 1.0000
8.000 0.8902 0.02127 0.01334 -0.0110 0.0178 1.0000
8.250 0.9085 0.02222 0.01438 -0.0097 0.0163 1.0000
8.500 0.9247 0.02344 0.01569 -0.0082 0.0152 1.0000
8.750 0.9417 0.02471 0.01711 -0.0068 0.0142 1.0000
9.000 0.9592 0.02592 0.01850 -0.0055 0.0134 1.0000
9.250 0.9765 0.02702 0.01974 -0.0042 0.0124 1.0000
9.500 0.9925 0.02814 0.02098 -0.0029 0.0117 1.0000
9.750 1.0066 0.02958 0.02258 -0.0014 0.0114 1.0000
10.000 1.0184 0.03119 0.02433 0.0003 0.0110 1.0000
10.250 1.0270 0.03325 0.02660 0.0023 0.0107 1.0000
10.500 1.0339 0.03529 0.02894 0.0047 0.0106 1.0000
10.750 1.0364 0.03762 0.03159 0.0073 0.0104 1.0000
11.000 1.0349 0.04018 0.03446 0.0099 0.0102 1.0000
11.250 1.0297 0.04298 0.03756 0.0124 0.0101 1.0000
11.500 1.0211 0.04605 0.04093 0.0146 0.0101 1.0000
11.750 1.0076 0.04968 0.04487 0.0162 0.0100 1.0000
12.000 0.9922 0.05370 0.04915 0.0170 0.0100 1.0000
12.250 0.9729 0.05853 0.05424 0.0166 0.0100 1.0000
12.500 0.9533 0.06399 0.05992 0.0148 0.0100 1.0000
12.750 0.9340 0.07017 0.06630 0.0116 0.0101 1.0000
13.000 0.9101 0.07832 0.07464 0.0062 0.0102 1.0000
13.250 0.8862 0.08819 0.08465 -0.0008 0.0103 1.0000
13.500 0.8564 0.10168 0.09823 -0.0098 0.0105 1.0000
13.750 0.8233 0.11658 0.11315 -0.0179 0.0107 1.0000
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Polar data table (+)
Polar graphs
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