GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 50,000 Max Cl/Cd: 27.88 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe481a-il-50000-n5.txt Download as CSV file: xf-goe481a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2800 0.12096 0.11391 -0.0311 0.9838 0.1536
-7.000 -0.2754 0.11797 0.11093 -0.0350 0.9758 0.1540
-6.750 -0.2687 0.11476 0.10773 -0.0386 0.9681 0.1541
-6.500 -0.2609 0.11147 0.10445 -0.0414 0.9596 0.1540
-6.250 -0.2576 0.10348 0.09634 -0.0453 0.9508 0.1175
-6.000 -0.2436 0.10013 0.09299 -0.0474 0.9430 0.1161
-5.750 -0.2346 0.09658 0.08944 -0.0501 0.9334 0.1148
-5.500 -0.2298 0.09287 0.08572 -0.0524 0.9222 0.1135
-5.250 -0.2397 0.08543 0.07807 -0.0601 0.9083 0.1081
-5.000 -0.2176 0.08169 0.07427 -0.0632 0.9013 0.1074
-4.750 -0.2102 0.07846 0.07100 -0.0638 0.8888 0.1068
-4.500 -0.1987 0.07473 0.06717 -0.0656 0.8779 0.1063
-4.250 -0.1807 0.07033 0.06259 -0.0690 0.8688 0.1066
-4.000 -0.1729 0.06638 0.05841 -0.0701 0.8560 0.1075
-3.750 -0.1491 0.06167 0.05335 -0.0735 0.8493 0.1081
-3.500 -0.1393 0.05913 0.05066 -0.0726 0.8360 0.1084
-3.250 -0.1190 0.05650 0.04783 -0.0731 0.8267 0.1089
-3.000 -0.0986 0.05419 0.04533 -0.0732 0.8167 0.1095
-2.750 -0.0797 0.05248 0.04349 -0.0727 0.8063 0.1110
-2.500 -0.0545 0.05043 0.04122 -0.0731 0.7978 0.1135
-2.250 -0.0368 0.04846 0.03893 -0.0723 0.7869 0.1156
-2.000 -0.0105 0.04586 0.03582 -0.0726 0.7794 0.1177
-1.750 0.0090 0.04443 0.03415 -0.0715 0.7688 0.1191
-1.500 0.0381 0.04314 0.03276 -0.0716 0.7611 0.1213
-1.250 0.0603 0.04214 0.03156 -0.0707 0.7513 0.1246
-1.000 0.0881 0.04053 0.02944 -0.0703 0.7433 0.1293
-0.750 0.1256 0.03914 0.02804 -0.0714 0.7389 0.1329
-0.500 0.1409 0.03870 0.02745 -0.0693 0.7258 0.1360
-0.250 0.1790 0.03723 0.02565 -0.0702 0.7209 0.1428
0.000 0.1969 0.03699 0.02540 -0.0686 0.7087 0.1477
0.250 0.2357 0.03574 0.02385 -0.0697 0.7030 0.1557
0.500 0.2599 0.03533 0.02344 -0.0689 0.6929 0.1630
0.750 0.2948 0.03449 0.02247 -0.0696 0.6852 0.1731
1.000 0.3444 0.03330 0.02114 -0.0725 0.6806 0.1880
1.250 0.3633 0.03349 0.02129 -0.0711 0.6680 0.1987
1.500 0.4121 0.03254 0.02028 -0.0741 0.6623 0.2169
1.750 0.4359 0.03260 0.02035 -0.0735 0.6514 0.2295
2.000 0.4778 0.03202 0.01972 -0.0754 0.6442 0.2466
2.250 0.5122 0.03177 0.01941 -0.0762 0.6358 0.2621
2.500 0.5406 0.03168 0.01938 -0.0762 0.6262 0.2758
2.750 0.5905 0.03089 0.01859 -0.0794 0.6204 0.2979
3.000 0.6010 0.03146 0.01928 -0.0768 0.6088 0.3124
3.500 0.7313 0.02984 0.01925 -0.0907 0.5912 1.0000
3.750 0.7631 0.03004 0.01919 -0.0910 0.5830 1.0000
4.000 0.7868 0.03049 0.01947 -0.0901 0.5746 1.0000
4.250 0.8042 0.03108 0.01995 -0.0883 0.5654 1.0000
4.500 0.8501 0.03101 0.01964 -0.0909 0.5591 1.0000
4.750 0.8451 0.03219 0.02085 -0.0857 0.5489 1.0000
5.000 0.8776 0.03241 0.02092 -0.0862 0.5416 1.0000
5.250 0.8931 0.03312 0.02158 -0.0842 0.5336 1.0000
5.500 0.9048 0.03393 0.02237 -0.0817 0.5251 1.0000
5.750 0.9461 0.03394 0.02221 -0.0835 0.5190 1.0000
6.000 0.9369 0.03538 0.02373 -0.0780 0.5098 1.0000
6.250 0.9614 0.03577 0.02405 -0.0773 0.5022 1.0000
6.500 0.9802 0.03632 0.02454 -0.0758 0.4943 1.0000
6.750 0.9808 0.03745 0.02569 -0.0718 0.4849 1.0000
7.000 1.0211 0.03706 0.02513 -0.0730 0.4770 1.0000
7.250 1.0028 0.03886 0.02705 -0.0667 0.4664 1.0000
7.500 1.0451 0.03826 0.02629 -0.0679 0.4588 1.0000
7.750 1.0223 0.04044 0.02861 -0.0615 0.4487 1.0000
8.000 1.0504 0.04044 0.02852 -0.0611 0.4414 1.0000
8.250 1.0465 0.04207 0.03022 -0.0573 0.4333 1.0000
8.500 1.0506 0.04333 0.03152 -0.0545 0.4253 1.0000
8.750 1.0930 0.04263 0.03070 -0.0555 0.4198 1.0000
9.000 1.0526 0.04646 0.03475 -0.0488 0.4098 1.0000
9.250 1.0802 0.04642 0.03466 -0.0483 0.4035 1.0000
9.500 1.0671 0.04904 0.03737 -0.0447 0.3952 1.0000
9.750 1.0660 0.05096 0.03936 -0.0422 0.3872 1.0000
10.000 1.1122 0.04953 0.03783 -0.0428 0.3824 1.0000
10.250 1.0518 0.05615 0.04469 -0.0375 0.3702 1.0000
10.500 1.0909 0.05487 0.04334 -0.0372 0.3654 1.0000
10.750 1.0364 0.06212 0.05079 -0.0339 0.3525 1.0000
11.000 1.0700 0.06103 0.04966 -0.0331 0.3476 1.0000
11.500 1.0446 0.06870 0.05749 -0.0305 0.3294 1.0000
11.750 1.0901 0.06620 0.05493 -0.0295 0.3267 1.0000
12.250 1.0333 0.07842 0.06735 -0.0284 0.3060 1.0000
12.750 1.0040 0.08854 0.07759 -0.0286 0.2883 1.0000
13.250 0.9611 0.10192 0.09110 -0.0308 0.2706 1.0000
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Polar data table (+)
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