GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 500,000 Max Cl/Cd: 91.95 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe381-il-500000-n5.txt Download as CSV file: xf-goe381-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1649 0.08869 0.08664 -0.0360 0.9330 0.0084
-8.500 -0.1609 0.08559 0.08353 -0.0365 0.9240 0.0084
-8.250 -0.1568 0.08246 0.08039 -0.0371 0.9149 0.0084
-8.000 -0.1524 0.07934 0.07725 -0.0377 0.9062 0.0084
-7.750 -0.1482 0.07621 0.07410 -0.0384 0.8974 0.0084
-7.250 -0.1388 0.06984 0.06768 -0.0401 0.8800 0.0084
-6.750 -0.1275 0.06324 0.06105 -0.0429 0.8630 0.0084
-6.250 -0.1104 0.05586 0.05364 -0.0460 0.8473 0.0077
-6.000 -0.1455 0.07073 0.06840 -0.0505 0.8681 0.0077
-5.750 -0.1245 0.06704 0.06468 -0.0549 0.8596 0.0069
-5.500 -0.1004 0.06301 0.06058 -0.0600 0.8516 0.0065
-5.250 -0.0743 0.05907 0.05657 -0.0649 0.8426 0.0065
-5.000 -0.0467 0.05536 0.05278 -0.0696 0.8328 0.0067
-4.750 -0.0169 0.05162 0.04894 -0.0743 0.8224 0.0076
-4.500 0.0147 0.04758 0.04476 -0.0791 0.8117 0.0078
-4.250 0.0470 0.04363 0.04069 -0.0834 0.8003 0.0077
-4.000 0.0810 0.03944 0.03631 -0.0876 0.7880 0.0078
-3.750 0.1174 0.03463 0.03125 -0.0917 0.7746 0.0083
-3.500 0.1491 0.03156 0.02797 -0.0940 0.7578 0.0089
-3.250 0.1771 0.03019 0.02642 -0.0950 0.7382 0.0102
-3.000 0.2128 0.02570 0.02154 -0.0972 0.7182 0.0116
-2.750 0.2466 0.02145 0.01680 -0.0986 0.6953 0.0133
-2.500 0.2721 0.02157 0.01677 -0.0985 0.6660 0.0145
-2.250 0.3017 0.01961 0.01443 -0.0988 0.6390 0.0171
-2.000 0.3335 0.01554 0.00973 -0.0991 0.6162 0.0211
-1.750 0.3595 0.01591 0.00993 -0.0991 0.5878 0.0222
-1.500 0.3866 0.01533 0.00908 -0.0990 0.5633 0.0239
-1.250 0.4144 0.01429 0.00773 -0.0990 0.5418 0.0266
-1.000 0.4421 0.01328 0.00639 -0.0989 0.5244 0.0277
-0.750 0.4699 0.01261 0.00549 -0.0989 0.5131 0.0282
-0.500 0.4975 0.01222 0.00493 -0.0988 0.5037 0.0288
-0.250 0.5251 0.01165 0.00419 -0.0987 0.4935 0.0287
0.000 0.5527 0.01121 0.00362 -0.0987 0.4840 0.0286
0.250 0.5801 0.01089 0.00319 -0.0986 0.4745 0.0286
0.500 0.6075 0.01064 0.00285 -0.0985 0.4639 0.0287
0.750 0.6349 0.01047 0.00261 -0.0985 0.4525 0.0290
1.000 0.6622 0.01039 0.00245 -0.0984 0.4392 0.0295
1.250 0.6894 0.01035 0.00234 -0.0983 0.4231 0.0302
1.500 0.7163 0.01026 0.00213 -0.0983 0.4029 0.0329
1.750 0.7429 0.01037 0.00212 -0.0981 0.3766 0.0347
2.000 0.7690 0.01057 0.00217 -0.0980 0.3465 0.0361
2.250 0.7948 0.01084 0.00226 -0.0978 0.3138 0.0372
2.750 0.8470 0.01128 0.00250 -0.0975 0.2730 0.0413
3.000 0.8735 0.01145 0.00263 -0.0973 0.2609 0.0452
3.250 0.9001 0.01159 0.00279 -0.0972 0.2514 0.0643
3.500 0.9265 0.01177 0.00296 -0.0971 0.2428 0.0837
3.750 0.9529 0.01194 0.00314 -0.0970 0.2352 0.0980
4.250 1.0058 0.01226 0.00351 -0.0968 0.2241 0.1211
4.500 1.0319 0.01244 0.00373 -0.0966 0.2174 0.1437
5.000 1.0786 0.01173 0.00432 -0.0957 0.1801 1.0000
5.250 1.1005 0.01249 0.00474 -0.0951 0.1296 1.0000
5.500 1.1240 0.01303 0.00519 -0.0946 0.1119 1.0000
5.750 1.1478 0.01351 0.00558 -0.0942 0.0965 1.0000
6.000 1.1651 0.01485 0.00652 -0.0929 0.0180 1.0000
6.250 1.1895 0.01521 0.00695 -0.0924 0.0131 1.0000
6.500 1.2134 0.01564 0.00749 -0.0919 0.0108 1.0000
6.750 1.2361 0.01621 0.00817 -0.0912 0.0090 1.0000
7.000 1.2588 0.01675 0.00882 -0.0905 0.0078 1.0000
7.250 1.2814 0.01727 0.00941 -0.0898 0.0068 1.0000
7.500 1.3028 0.01793 0.01015 -0.0890 0.0062 1.0000
7.750 1.3214 0.01886 0.01122 -0.0878 0.0056 1.0000
8.000 1.3393 0.01984 0.01231 -0.0865 0.0053 1.0000
8.250 1.3574 0.02071 0.01328 -0.0852 0.0049 1.0000
8.500 1.3754 0.02151 0.01416 -0.0840 0.0044 1.0000
8.750 1.3921 0.02236 0.01509 -0.0826 0.0040 1.0000
9.000 1.4056 0.02342 0.01624 -0.0808 0.0038 1.0000
9.250 1.4135 0.02477 0.01769 -0.0783 0.0036 1.0000
9.500 1.4142 0.02641 0.01945 -0.0748 0.0034 1.0000
9.750 1.4178 0.02791 0.02112 -0.0719 0.0034 1.0000
10.000 1.4192 0.02969 0.02303 -0.0691 0.0032 1.0000
10.250 1.4190 0.03173 0.02520 -0.0666 0.0031 1.0000
10.500 1.4179 0.03401 0.02762 -0.0642 0.0031 1.0000
10.750 1.4166 0.03648 0.03021 -0.0622 0.0030 1.0000
11.000 1.4152 0.03910 0.03294 -0.0603 0.0029 1.0000
11.250 1.4145 0.04178 0.03574 -0.0586 0.0029 1.0000
11.500 1.4147 0.04449 0.03857 -0.0570 0.0028 1.0000
11.750 1.4159 0.04718 0.04137 -0.0555 0.0028 1.0000
12.000 1.4178 0.04983 0.04415 -0.0543 0.0027 1.0000
12.250 1.4191 0.05255 0.04699 -0.0535 0.0025 1.0000
12.500 1.4190 0.05541 0.04997 -0.0532 0.0024 1.0000
12.750 1.4179 0.05849 0.05316 -0.0532 0.0023 1.0000
13.000 1.4157 0.06183 0.05662 -0.0532 0.0023 1.0000
13.250 1.4122 0.06539 0.06031 -0.0536 0.0022 1.0000
13.500 1.4071 0.06927 0.06432 -0.0542 0.0022 1.0000
13.750 1.4008 0.07347 0.06865 -0.0547 0.0021 1.0000
14.250 1.3854 0.08265 0.07816 -0.0554 0.0020 1.0000
14.500 1.3774 0.08756 0.08324 -0.0562 0.0020 1.0000
14.750 1.3681 0.09283 0.08870 -0.0574 0.0020 1.0000
15.000 1.3573 0.09847 0.09456 -0.0591 0.0020 1.0000
15.250 1.3456 0.10448 0.10076 -0.0613 0.0019 1.0000
15.500 1.3334 0.11080 0.10724 -0.0640 0.0019 1.0000
15.750 1.3208 0.11740 0.11401 -0.0671 0.0019 1.0000
16.000 1.3084 0.12420 0.12096 -0.0705 0.0019 1.0000
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Polar data table (+)
Polar graphs
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