GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 565 AIRFOIL (goe565-il) Reynolds number: 50,000 Max Cl/Cd: 37.39 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe565-il-50000.txt Download as CSV file: xf-goe565-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 565 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4081 0.10230 0.09511 -0.0170 1.0000 0.2575
-8.250 -0.4083 0.09955 0.09244 -0.0167 1.0000 0.2675
-8.000 -0.4270 0.09919 0.09223 -0.0165 1.0000 0.2776
-7.750 -0.4132 0.09507 0.08811 -0.0151 1.0000 0.2913
-7.500 -0.4069 0.09176 0.08484 -0.0137 1.0000 0.3049
-7.250 -0.4063 0.08917 0.08232 -0.0121 1.0000 0.3198
-7.000 -0.4104 0.08702 0.08027 -0.0100 1.0000 0.3357
-6.750 -0.4164 0.08500 0.07836 -0.0076 1.0000 0.3516
-6.500 -0.4252 0.08314 0.07663 -0.0051 1.0000 0.3675
-6.250 -0.4245 0.08028 0.07385 -0.0028 1.0000 0.3846
-6.000 -0.4115 0.07675 0.07033 -0.0003 1.0000 0.4032
-5.750 -0.4116 0.07446 0.06811 0.0027 1.0000 0.4247
-5.500 -0.4070 0.07178 0.06549 0.0061 1.0000 0.4507
-5.250 -0.4061 0.06944 0.06320 0.0098 1.0000 0.4792
-4.750 -0.3966 0.04628 0.03863 -0.0397 1.0000 0.1905
-4.500 -0.3772 0.04243 0.03452 -0.0401 1.0000 0.1839
-4.250 -0.3520 0.03761 0.02884 -0.0422 1.0000 0.1730
-4.000 -0.3292 0.03470 0.02536 -0.0424 1.0000 0.1740
-3.750 -0.3068 0.03229 0.02262 -0.0421 1.0000 0.1768
-3.500 -0.2827 0.03013 0.02004 -0.0417 1.0000 0.1778
-3.250 -0.2590 0.02845 0.01810 -0.0411 1.0000 0.1815
-3.000 -0.2344 0.02712 0.01631 -0.0406 1.0000 0.1896
-2.750 -0.2111 0.02587 0.01504 -0.0398 1.0000 0.1966
-2.500 -0.1852 0.02478 0.01360 -0.0393 1.0000 0.2042
-2.250 -0.1619 0.02389 0.01270 -0.0384 1.0000 0.2165
-2.000 -0.1388 0.02318 0.01204 -0.0375 1.0000 0.2365
-1.750 -0.1130 0.02243 0.01133 -0.0370 1.0000 0.2658
-1.500 -0.0863 0.02104 0.01052 -0.0366 1.0000 0.3587
-1.250 -0.0576 0.01813 0.00976 -0.0344 1.0000 1.0000
-1.000 -0.0356 0.01838 0.00953 -0.0339 1.0000 1.0000
-0.750 -0.0145 0.01865 0.00946 -0.0333 1.0000 1.0000
-0.500 0.0062 0.01897 0.00947 -0.0327 1.0000 1.0000
-0.250 0.0266 0.01931 0.00958 -0.0321 1.0000 1.0000
0.000 0.0467 0.01969 0.00976 -0.0316 1.0000 1.0000
0.250 0.0665 0.02011 0.01001 -0.0310 1.0000 1.0000
0.500 0.0860 0.02058 0.01032 -0.0305 1.0000 1.0000
0.750 0.1051 0.02108 0.01070 -0.0300 1.0000 1.0000
1.000 0.1238 0.02165 0.01116 -0.0295 1.0000 1.0000
1.250 0.1420 0.02226 0.01170 -0.0291 1.0000 1.0000
1.500 0.1598 0.02294 0.01231 -0.0288 1.0000 1.0000
1.750 0.1770 0.02369 0.01301 -0.0285 1.0000 1.0000
2.000 0.1937 0.02451 0.01380 -0.0283 1.0000 1.0000
2.250 0.2487 0.02612 0.01541 -0.0352 0.9826 1.0000
2.500 0.3023 0.02743 0.01676 -0.0416 0.9604 1.0000
2.750 0.3561 0.02864 0.01803 -0.0475 0.9393 1.0000
3.000 0.4034 0.02956 0.01907 -0.0520 0.9163 1.0000
3.250 0.4527 0.03033 0.01997 -0.0564 0.8932 1.0000
3.500 0.5126 0.03061 0.02045 -0.0615 0.8669 1.0000
3.750 0.5688 0.03023 0.02029 -0.0649 0.8357 1.0000
4.000 0.6301 0.02927 0.01959 -0.0681 0.8061 1.0000
4.250 0.6882 0.02820 0.01884 -0.0706 0.7808 1.0000
4.500 0.7342 0.02726 0.01815 -0.0710 0.7527 1.0000
4.750 0.7810 0.02609 0.01726 -0.0710 0.7223 1.0000
5.000 0.8177 0.02531 0.01665 -0.0695 0.6853 1.0000
5.250 0.8534 0.02460 0.01603 -0.0677 0.6432 1.0000
5.500 0.8825 0.02436 0.01581 -0.0653 0.5950 1.0000
5.750 0.9105 0.02436 0.01557 -0.0628 0.5434 1.0000
6.000 0.9296 0.02486 0.01586 -0.0597 0.4892 1.0000
6.250 0.9463 0.02541 0.01612 -0.0565 0.4375 1.0000
6.500 0.9591 0.02603 0.01658 -0.0532 0.3873 1.0000
6.750 0.9723 0.02690 0.01718 -0.0501 0.3381 1.0000
7.000 0.9825 0.02830 0.01827 -0.0468 0.2793 1.0000
7.250 0.9921 0.03061 0.02009 -0.0434 0.2118 1.0000
7.500 1.0126 0.03323 0.02234 -0.0419 0.1734 1.0000
7.750 1.0382 0.03596 0.02512 -0.0410 0.1532 1.0000
8.000 1.0599 0.03842 0.02772 -0.0399 0.1390 1.0000
8.250 1.0818 0.04140 0.03094 -0.0388 0.1305 1.0000
8.500 1.1016 0.04406 0.03380 -0.0375 0.1227 1.0000
8.750 1.1143 0.04730 0.03748 -0.0355 0.1172 1.0000
9.000 1.1233 0.05097 0.04168 -0.0333 0.1142 1.0000
9.250 1.1294 0.05489 0.04605 -0.0311 0.1125 1.0000
9.500 1.1346 0.05865 0.05017 -0.0290 0.1105 1.0000
9.750 1.1462 0.06253 0.05408 -0.0279 0.1071 1.0000
10.000 1.1378 0.06691 0.05890 -0.0253 0.1067 1.0000
10.250 1.1263 0.07146 0.06379 -0.0230 0.1068 1.0000
10.500 1.1158 0.07623 0.06880 -0.0213 0.1073 1.0000
10.750 1.0284 0.08318 0.07623 -0.0190 0.1161 1.0000
11.000 1.0039 0.08943 0.08255 -0.0204 0.1182 1.0000
11.250 0.9879 0.09590 0.08905 -0.0225 0.1197 1.0000
11.500 0.9789 0.10239 0.09556 -0.0245 0.1206 1.0000
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Polar data table (+)
Polar graphs
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