GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 394 AIRFOIL (goe394-il) Reynolds number: 500,000 Max Cl/Cd: 116.57 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe394-il-500000.txt Download as CSV file: xf-goe394-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 394 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3232 0.09918 0.09692 -0.0221 0.8951 0.0214
-8.000 -0.3171 0.09612 0.09377 -0.0238 0.8703 0.0214
-7.750 -0.3098 0.09169 0.08929 -0.0219 0.8580 0.0219
-7.500 -0.2996 0.08918 0.08671 -0.0224 0.8463 0.0223
-7.250 -0.2891 0.08670 0.08417 -0.0239 0.8369 0.0228
-7.000 -0.2753 0.08385 0.08128 -0.0265 0.8296 0.0235
-6.750 -0.2599 0.08075 0.07813 -0.0300 0.8232 0.0246
-6.500 -0.2307 0.07648 0.07379 -0.0416 0.8173 0.0269
-6.250 -0.2044 0.07232 0.06958 -0.0489 0.8124 0.0271
-6.000 -0.1912 0.06692 0.06414 -0.0519 0.8081 0.0278
-5.750 -0.1743 0.06470 0.06187 -0.0523 0.8036 0.0283
-5.500 -0.1526 0.06221 0.05936 -0.0548 0.7984 0.0292
-5.250 -0.1271 0.05928 0.05636 -0.0589 0.7936 0.0308
-4.750 -0.0508 0.04882 0.04567 -0.0771 0.7859 0.0356
-4.500 -0.0284 0.04710 0.04391 -0.0779 0.7819 0.0366
-4.250 -0.0006 0.04491 0.04165 -0.0805 0.7782 0.0382
-4.000 0.0574 0.03936 0.03581 -0.0920 0.7751 0.0436
-3.750 0.0779 0.03650 0.03292 -0.0933 0.7721 0.0454
-3.500 0.1044 0.03505 0.03143 -0.0944 0.7687 0.0470
-3.250 0.1528 0.03176 0.02781 -0.1001 0.7653 0.0535
-3.000 0.1982 0.01369 0.00805 -0.1096 0.7631 0.0394
-2.750 0.2268 0.01249 0.00652 -0.1098 0.7598 0.0397
-2.500 0.2554 0.01172 0.00556 -0.1098 0.7563 0.0403
-2.250 0.2839 0.01118 0.00489 -0.1098 0.7527 0.0415
-2.000 0.3123 0.01069 0.00427 -0.1097 0.7494 0.0422
-1.750 0.3406 0.01031 0.00378 -0.1096 0.7461 0.0429
-1.500 0.3688 0.01005 0.00343 -0.1095 0.7428 0.0435
-1.250 0.3973 0.00962 0.00297 -0.1094 0.7392 0.0452
-1.000 0.4256 0.00939 0.00273 -0.1093 0.7353 0.0476
-0.750 0.4537 0.00924 0.00255 -0.1091 0.7313 0.0508
-0.500 0.4819 0.00913 0.00247 -0.1090 0.7275 0.0595
-0.250 0.5103 0.00925 0.00269 -0.1088 0.7230 0.0814
0.000 0.5386 0.00947 0.00288 -0.1086 0.7181 0.0918
0.250 0.5665 0.00966 0.00302 -0.1084 0.7136 0.0984
0.500 0.5946 0.00962 0.00300 -0.1083 0.7083 0.1031
0.750 0.6224 0.00955 0.00295 -0.1082 0.7025 0.1075
1.000 0.6502 0.00956 0.00295 -0.1080 0.6970 0.1119
1.250 0.6782 0.00945 0.00286 -0.1079 0.6901 0.1160
1.500 0.7058 0.00931 0.00272 -0.1077 0.6835 0.1193
1.750 0.7337 0.00917 0.00266 -0.1075 0.6750 0.1224
2.000 0.7614 0.00910 0.00259 -0.1073 0.6658 0.1261
2.250 0.7891 0.00899 0.00248 -0.1071 0.6528 0.1276
2.500 0.8168 0.00883 0.00236 -0.1069 0.6343 0.1292
2.750 0.8442 0.00871 0.00224 -0.1067 0.6070 0.1318
3.000 0.8703 0.00880 0.00216 -0.1062 0.5608 0.1353
3.250 0.8958 0.00910 0.00226 -0.1058 0.5234 0.1384
3.500 0.9220 0.00934 0.00241 -0.1055 0.5007 0.1411
3.750 0.9484 0.00956 0.00258 -0.1052 0.4816 0.1448
4.000 0.9749 0.00976 0.00276 -0.1050 0.4651 0.1516
4.250 1.0015 0.00992 0.00295 -0.1047 0.4513 0.1697
4.500 1.0270 0.00881 0.00329 -0.1046 0.4396 1.0000
4.750 1.0535 0.00905 0.00348 -0.1043 0.4278 1.0000
5.250 1.1063 0.00952 0.00388 -0.1038 0.4029 1.0000
5.500 1.1327 0.00973 0.00410 -0.1035 0.3906 1.0000
5.750 1.1588 0.00999 0.00432 -0.1032 0.3749 1.0000
6.000 1.1842 0.01030 0.00455 -0.1029 0.3518 1.0000
6.250 1.2091 0.01067 0.00481 -0.1025 0.3234 1.0000
6.500 1.2335 0.01110 0.00513 -0.1020 0.2919 1.0000
6.750 1.2565 0.01171 0.00554 -0.1014 0.2491 1.0000
7.000 1.2757 0.01282 0.00622 -0.1004 0.1763 1.0000
7.250 1.2952 0.01386 0.00697 -0.0995 0.1297 1.0000
7.500 1.3171 0.01456 0.00759 -0.0987 0.1104 1.0000
7.750 1.3393 0.01518 0.00815 -0.0980 0.0918 1.0000
8.000 1.3561 0.01646 0.00905 -0.0967 0.0435 1.0000
8.250 1.3740 0.01756 0.01007 -0.0953 0.0286 1.0000
8.500 1.3921 0.01859 0.01111 -0.0940 0.0240 1.0000
8.750 1.4116 0.01936 0.01199 -0.0928 0.0222 1.0000
9.000 1.4302 0.02018 0.01287 -0.0916 0.0205 1.0000
9.250 1.4459 0.02122 0.01396 -0.0900 0.0189 1.0000
9.500 1.4568 0.02265 0.01548 -0.0878 0.0177 1.0000
9.750 1.4722 0.02354 0.01647 -0.0861 0.0169 1.0000
10.000 1.4840 0.02460 0.01763 -0.0841 0.0162 1.0000
10.250 1.4925 0.02575 0.01886 -0.0815 0.0156 1.0000
10.500 1.4997 0.02703 0.02022 -0.0791 0.0151 1.0000
10.750 1.5054 0.02850 0.02177 -0.0769 0.0146 1.0000
11.000 1.5083 0.03033 0.02367 -0.0745 0.0142 1.0000
11.250 1.5067 0.03273 0.02617 -0.0721 0.0137 1.0000
11.500 1.5049 0.03536 0.02892 -0.0696 0.0134 1.0000
11.750 1.5137 0.03690 0.03058 -0.0684 0.0131 1.0000
12.000 1.5205 0.03867 0.03249 -0.0671 0.0127 1.0000
12.250 1.5258 0.04067 0.03460 -0.0658 0.0123 1.0000
12.500 1.5296 0.04287 0.03692 -0.0645 0.0120 1.0000
12.750 1.5326 0.04518 0.03934 -0.0633 0.0117 1.0000
13.000 1.5349 0.04762 0.04190 -0.0621 0.0115 1.0000
13.250 1.5361 0.05020 0.04459 -0.0611 0.0113 1.0000
13.500 1.5364 0.05291 0.04742 -0.0601 0.0110 1.0000
13.750 1.5357 0.05577 0.05040 -0.0593 0.0108 1.0000
14.000 1.5338 0.05882 0.05356 -0.0586 0.0107 1.0000
14.250 1.5307 0.06209 0.05694 -0.0579 0.0105 1.0000
14.500 1.5259 0.06566 0.06065 -0.0573 0.0104 1.0000
14.750 1.5188 0.06961 0.06474 -0.0568 0.0103 1.0000
15.000 1.5094 0.07409 0.06939 -0.0566 0.0102 1.0000
15.250 1.4974 0.07908 0.07458 -0.0569 0.0101 1.0000
15.500 1.4832 0.08462 0.08032 -0.0577 0.0101 1.0000
15.750 1.4679 0.09061 0.08651 -0.0593 0.0100 1.0000
16.000 1.4529 0.09678 0.09287 -0.0614 0.0100 1.0000
16.250 1.4373 0.10337 0.09965 -0.0641 0.0100 1.0000
16.500 1.4220 0.11020 0.10666 -0.0673 0.0100 1.0000
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Polar data table (+)
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