GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 100,000 Max Cl/Cd: 46.31 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe481a-il-100000-n5.txt Download as CSV file: xf-goe481a-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1587 0.09800 0.09243 -0.0660 0.9468 0.0776
-7.250 -0.1620 0.09424 0.08869 -0.0677 0.9393 0.0767
-6.750 -0.1957 0.08375 0.07818 -0.0743 0.9206 0.0747
-6.500 -0.1912 0.08020 0.07462 -0.0761 0.9130 0.0744
-6.250 -0.1871 0.07604 0.07043 -0.0785 0.9044 0.0741
-6.000 -0.1873 0.07165 0.06599 -0.0802 0.8944 0.0739
-5.750 -0.1798 0.06612 0.06035 -0.0840 0.8867 0.0737
-5.500 -0.1857 0.06008 0.05412 -0.0855 0.8746 0.0741
-5.250 -0.1811 0.05143 0.04502 -0.0899 0.8681 0.0751
-5.000 -0.1723 0.04987 0.04342 -0.0879 0.8565 0.0757
-4.750 -0.1532 0.04571 0.03898 -0.0892 0.8510 0.0762
-4.500 -0.1463 0.04270 0.03571 -0.0874 0.8396 0.0767
-4.250 -0.1262 0.03913 0.03178 -0.0877 0.8336 0.0776
-4.000 -0.1139 0.03679 0.02913 -0.0858 0.8231 0.0788
-3.750 -0.0944 0.03363 0.02543 -0.0851 0.8163 0.0809
-3.500 -0.0768 0.03139 0.02274 -0.0835 0.8073 0.0826
-3.250 -0.0516 0.03051 0.02180 -0.0828 0.7989 0.0835
-3.000 -0.0239 0.02944 0.02062 -0.0825 0.7918 0.0847
-2.750 -0.0018 0.02849 0.01951 -0.0813 0.7811 0.0862
-2.500 0.0294 0.02712 0.01786 -0.0815 0.7747 0.0884
-2.250 0.0522 0.02618 0.01671 -0.0802 0.7629 0.0906
-2.000 0.0857 0.02557 0.01611 -0.0808 0.7551 0.0926
-1.750 0.1139 0.02495 0.01539 -0.0804 0.7437 0.0951
-1.500 0.1480 0.02391 0.01412 -0.0810 0.7345 0.0984
-1.250 0.1819 0.02332 0.01350 -0.0817 0.7236 0.1009
-1.000 0.2154 0.02281 0.01292 -0.0823 0.7122 0.1047
-0.750 0.2555 0.02215 0.01212 -0.0840 0.7017 0.1101
-0.500 0.2863 0.02185 0.01174 -0.0843 0.6888 0.1154
-0.250 0.3250 0.02137 0.01115 -0.0859 0.6775 0.1217
0.000 0.3574 0.02109 0.01073 -0.0864 0.6650 0.1301
0.250 0.3899 0.02090 0.01048 -0.0870 0.6535 0.1384
0.500 0.4248 0.02065 0.01015 -0.0881 0.6425 0.1474
0.750 0.4522 0.02056 0.00996 -0.0878 0.6313 0.1562
1.000 0.4865 0.02038 0.00971 -0.0888 0.6212 0.1658
1.250 0.5101 0.02033 0.00968 -0.0879 0.6104 0.1737
1.500 0.5428 0.02029 0.00951 -0.0886 0.6010 0.1849
1.750 0.5658 0.02025 0.00957 -0.0876 0.5912 0.1941
2.000 0.5951 0.02023 0.00949 -0.0878 0.5823 0.2042
2.250 0.6202 0.02024 0.00952 -0.0871 0.5732 0.2121
2.500 0.6458 0.02030 0.00953 -0.0865 0.5640 0.2196
2.750 0.6767 0.02034 0.00955 -0.0870 0.5556 0.2277
3.000 0.7008 0.02048 0.00970 -0.0863 0.5469 0.2367
3.250 0.7340 0.02054 0.00973 -0.0872 0.5395 0.2488
3.500 0.7554 0.02070 0.00994 -0.0860 0.5311 0.2637
3.750 0.7811 0.02076 0.01011 -0.0856 0.5228 0.2982
4.000 0.9057 0.02017 0.01100 -0.1062 0.5084 1.0000
4.250 0.9273 0.02044 0.01112 -0.1049 0.5006 1.0000
4.500 0.9450 0.02074 0.01134 -0.1028 0.4922 1.0000
4.750 0.9617 0.02103 0.01155 -0.1005 0.4836 1.0000
5.000 0.9810 0.02131 0.01171 -0.0988 0.4754 1.0000
5.250 0.9946 0.02163 0.01202 -0.0960 0.4664 1.0000
5.500 1.0151 0.02193 0.01218 -0.0945 0.4592 1.0000
5.750 1.0294 0.02228 0.01254 -0.0920 0.4510 1.0000
6.000 1.0456 0.02261 0.01281 -0.0898 0.4430 1.0000
6.250 1.0627 0.02295 0.01309 -0.0878 0.4356 1.0000
6.500 1.0768 0.02334 0.01348 -0.0853 0.4276 1.0000
6.750 1.0953 0.02368 0.01374 -0.0836 0.4210 1.0000
7.000 1.1103 0.02411 0.01419 -0.0813 0.4139 1.0000
7.250 1.1254 0.02453 0.01460 -0.0791 0.4069 1.0000
7.500 1.1443 0.02490 0.01488 -0.0776 0.4009 1.0000
7.750 1.1564 0.02541 0.01546 -0.0750 0.3934 1.0000
8.000 1.1711 0.02586 0.01591 -0.0728 0.3866 1.0000
8.250 1.1876 0.02631 0.01629 -0.0709 0.3804 1.0000
8.500 1.1997 0.02689 0.01695 -0.0685 0.3734 1.0000
8.750 1.2140 0.02740 0.01744 -0.0664 0.3670 1.0000
9.000 1.2290 0.02793 0.01795 -0.0645 0.3610 1.0000
9.250 1.2399 0.02860 0.01870 -0.0620 0.3539 1.0000
9.500 1.2533 0.02918 0.01926 -0.0599 0.3476 1.0000
9.750 1.2658 0.02984 0.01993 -0.0578 0.3413 1.0000
10.000 1.2749 0.03062 0.02079 -0.0553 0.3340 1.0000
10.250 1.2872 0.03127 0.02138 -0.0532 0.3273 1.0000
10.500 1.2943 0.03218 0.02239 -0.0506 0.3198 1.0000
10.750 1.3017 0.03306 0.02329 -0.0481 0.3121 1.0000
11.000 1.3099 0.03397 0.02419 -0.0457 0.3047 1.0000
11.250 1.3147 0.03509 0.02539 -0.0432 0.2967 1.0000
11.500 1.3226 0.03604 0.02628 -0.0410 0.2896 1.0000
11.750 1.3242 0.03745 0.02783 -0.0384 0.2810 1.0000
12.000 1.3296 0.03864 0.02900 -0.0363 0.2738 1.0000
12.250 1.3321 0.04014 0.03058 -0.0341 0.2662 1.0000
12.500 1.3346 0.04166 0.03213 -0.0320 0.2587 1.0000
12.750 1.3366 0.04330 0.03380 -0.0301 0.2514 1.0000
13.000 1.3371 0.04514 0.03572 -0.0282 0.2441 1.0000
13.250 1.3398 0.04685 0.03740 -0.0266 0.2381 1.0000
13.500 1.3396 0.04898 0.03965 -0.0251 0.2314 1.0000
13.750 1.3408 0.05099 0.04168 -0.0238 0.2258 1.0000
14.000 1.3427 0.05303 0.04374 -0.0226 0.2208 1.0000
14.250 1.3421 0.05543 0.04625 -0.0216 0.2154 1.0000
14.500 1.3425 0.05773 0.04858 -0.0206 0.2104 1.0000
14.750 1.3449 0.05987 0.05072 -0.0198 0.2062 1.0000
15.000 1.3423 0.06271 0.05370 -0.0192 0.2014 1.0000
15.250 1.3416 0.06532 0.05636 -0.0186 0.1970 1.0000
15.500 1.3453 0.06737 0.05837 -0.0180 0.1930 1.0000
15.750 1.3414 0.07054 0.06166 -0.0178 0.1887 1.0000
16.000 1.3372 0.07377 0.06501 -0.0176 0.1843 1.0000
16.250 1.3385 0.07627 0.06753 -0.0173 0.1804 1.0000
16.500 1.3430 0.07833 0.06956 -0.0170 0.1767 1.0000
16.750 1.3330 0.08251 0.07392 -0.0174 0.1724 1.0000
17.000 1.3287 0.08592 0.07742 -0.0176 0.1683 1.0000
17.250 1.3338 0.08796 0.07944 -0.0174 0.1645 1.0000
17.500 1.3328 0.09094 0.08249 -0.0176 0.1610 1.0000
17.750 1.3190 0.09588 0.08762 -0.0186 0.1568 1.0000
18.000 1.3150 0.09938 0.09118 -0.0192 0.1527 1.0000
18.250 1.3263 0.10050 0.09223 -0.0189 0.1493 1.0000
18.500 1.3088 0.10621 0.09815 -0.0205 0.1455 1.0000
18.750 1.2917 0.11194 0.10405 -0.0223 0.1413 1.0000
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