GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 50,000 Max Cl/Cd: 34.62 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe285-il-50000-n5.txt Download as CSV file: xf-goe285-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3487 0.11069 0.10317 -0.0283 1.0000 0.1336
-9.000 -0.3464 0.10758 0.10010 -0.0291 1.0000 0.1340
-8.750 -0.3812 0.09927 0.09187 -0.0382 1.0000 0.0880
-8.500 -0.3669 0.09628 0.08887 -0.0364 1.0000 0.0864
-8.250 -0.3671 0.09320 0.08587 -0.0363 1.0000 0.0855
-8.000 -0.3724 0.09023 0.08300 -0.0361 1.0000 0.0847
-7.750 -0.3799 0.08718 0.08006 -0.0362 1.0000 0.0839
-7.500 -0.3867 0.08386 0.07683 -0.0367 1.0000 0.0830
-7.250 -0.3943 0.08044 0.07347 -0.0372 1.0000 0.0820
-7.000 -0.4028 0.07683 0.06990 -0.0375 1.0000 0.0808
-6.500 -0.4304 0.06561 0.05832 -0.0411 1.0000 0.0760
-6.250 -0.4288 0.06268 0.05532 -0.0400 1.0000 0.0757
-6.000 -0.4260 0.05963 0.05216 -0.0392 1.0000 0.0755
-5.750 -0.4214 0.05648 0.04884 -0.0385 1.0000 0.0753
-5.500 -0.4145 0.05331 0.04543 -0.0380 1.0000 0.0752
-5.250 -0.3851 0.04840 0.03992 -0.0423 0.9932 0.0759
-5.000 -0.3534 0.04612 0.03754 -0.0451 0.9857 0.0778
-4.750 -0.3209 0.04367 0.03484 -0.0479 0.9777 0.0797
-4.500 -0.2864 0.04077 0.03151 -0.0508 0.9703 0.0810
-4.250 -0.2526 0.03813 0.02841 -0.0532 0.9619 0.0824
-4.000 -0.2180 0.03577 0.02557 -0.0553 0.9533 0.0845
-3.750 -0.1778 0.03363 0.02287 -0.0581 0.9453 0.0885
-3.500 -0.1431 0.03248 0.02167 -0.0598 0.9338 0.0927
-3.250 -0.1048 0.03100 0.01987 -0.0618 0.9233 0.0976
-3.000 -0.0624 0.02957 0.01823 -0.0644 0.9145 0.1036
-2.750 -0.0275 0.02866 0.01714 -0.0656 0.9029 0.1133
-2.500 0.0129 0.02772 0.01616 -0.0677 0.8945 0.1256
-2.250 0.0486 0.02698 0.01535 -0.0690 0.8841 0.1421
-2.000 0.0827 0.02637 0.01473 -0.0700 0.8734 0.1634
-1.750 0.1209 0.02562 0.01403 -0.0717 0.8646 0.1871
-1.500 0.1514 0.02504 0.01346 -0.0719 0.8523 0.2061
-1.250 0.1852 0.02441 0.01286 -0.0727 0.8419 0.2308
-1.000 0.2176 0.02371 0.01234 -0.0732 0.8309 0.2654
-0.750 0.2441 0.02287 0.01204 -0.0729 0.8181 0.3472
-0.500 0.3158 0.02073 0.01160 -0.0790 0.8113 1.0000
-0.250 0.3415 0.02082 0.01140 -0.0782 0.7962 1.0000
0.000 0.3674 0.02090 0.01124 -0.0774 0.7813 1.0000
0.250 0.3940 0.02096 0.01108 -0.0767 0.7658 1.0000
0.500 0.4203 0.02096 0.01087 -0.0758 0.7488 1.0000
0.750 0.4463 0.02094 0.01065 -0.0747 0.7305 1.0000
1.000 0.4720 0.02092 0.01043 -0.0736 0.7119 1.0000
1.250 0.4977 0.02091 0.01023 -0.0724 0.6933 1.0000
1.500 0.5232 0.02096 0.01009 -0.0714 0.6754 1.0000
1.750 0.5484 0.02106 0.01003 -0.0704 0.6580 1.0000
2.000 0.5734 0.02122 0.01003 -0.0694 0.6410 1.0000
2.250 0.5981 0.02141 0.01009 -0.0684 0.6240 1.0000
2.500 0.6225 0.02165 0.01021 -0.0675 0.6071 1.0000
2.750 0.6466 0.02192 0.01037 -0.0665 0.5904 1.0000
3.000 0.6705 0.02221 0.01056 -0.0656 0.5737 1.0000
3.250 0.6942 0.02253 0.01080 -0.0646 0.5573 1.0000
3.500 0.7178 0.02286 0.01105 -0.0637 0.5413 1.0000
3.750 0.7415 0.02321 0.01133 -0.0628 0.5259 1.0000
4.000 0.7652 0.02359 0.01165 -0.0619 0.5114 1.0000
4.250 0.7894 0.02399 0.01197 -0.0611 0.4980 1.0000
4.500 0.8141 0.02438 0.01227 -0.0604 0.4856 1.0000
4.750 0.8379 0.02484 0.01270 -0.0596 0.4729 1.0000
5.000 0.8613 0.02537 0.01321 -0.0588 0.4606 1.0000
5.250 0.8857 0.02588 0.01366 -0.0582 0.4499 1.0000
5.500 0.9099 0.02643 0.01419 -0.0576 0.4395 1.0000
5.750 0.9331 0.02709 0.01488 -0.0569 0.4297 1.0000
6.000 0.9584 0.02768 0.01544 -0.0564 0.4216 1.0000
6.250 0.9811 0.02845 0.01631 -0.0558 0.4134 1.0000
6.500 1.0054 0.02916 0.01706 -0.0553 0.4063 1.0000
6.750 1.0297 0.02993 0.01787 -0.0549 0.4000 1.0000
7.000 1.0508 0.03083 0.01894 -0.0541 0.3930 1.0000
7.250 1.0757 0.03155 0.01969 -0.0537 0.3873 1.0000
7.500 1.0963 0.03254 0.02083 -0.0529 0.3813 1.0000
7.750 1.1164 0.03358 0.02206 -0.0521 0.3756 1.0000
8.000 1.1400 0.03446 0.02304 -0.0517 0.3712 1.0000
8.250 1.1609 0.03548 0.02419 -0.0509 0.3662 1.0000
8.500 1.1756 0.03671 0.02566 -0.0495 0.3595 1.0000
8.750 1.1999 0.03727 0.02628 -0.0489 0.3531 1.0000
9.000 1.2111 0.03854 0.02780 -0.0471 0.3455 1.0000
9.250 1.2321 0.03901 0.02833 -0.0460 0.3374 1.0000
9.500 1.2414 0.04010 0.02963 -0.0439 0.3282 1.0000
9.750 1.2632 0.04012 0.02964 -0.0427 0.3183 1.0000
10.000 1.2678 0.04123 0.03099 -0.0400 0.3081 1.0000
10.250 1.2774 0.04189 0.03177 -0.0378 0.2978 1.0000
10.500 1.2934 0.04198 0.03183 -0.0359 0.2870 1.0000
10.750 1.2893 0.04353 0.03367 -0.0327 0.2776 1.0000
11.000 1.2921 0.04436 0.03458 -0.0298 0.2676 1.0000
11.250 1.2954 0.04516 0.03542 -0.0272 0.2569 1.0000
11.500 1.2843 0.04745 0.03794 -0.0244 0.2476 1.0000
11.750 1.2822 0.04904 0.03960 -0.0224 0.2371 1.0000
12.000 1.2736 0.05158 0.04232 -0.0208 0.2272 1.0000
12.250 1.2615 0.05490 0.04584 -0.0198 0.2177 1.0000
12.500 1.2547 0.05773 0.04876 -0.0192 0.2069 1.0000
12.750 1.2339 0.06293 0.05424 -0.0198 0.1965 1.0000
13.000 1.2107 0.06899 0.06053 -0.0212 0.1861 1.0000
13.250 1.1868 0.07558 0.06730 -0.0231 0.1751 1.0000
13.500 1.1630 0.08252 0.07438 -0.0254 0.1637 1.0000
13.750 1.1483 0.08807 0.07998 -0.0272 0.1509 1.0000
14.000 1.1541 0.08973 0.08152 -0.0270 0.1362 1.0000
14.250 1.1564 0.09196 0.08349 -0.0268 0.1248 1.0000
14.500 1.1555 0.09477 0.08600 -0.0269 0.1161 1.0000
14.750 1.1456 0.09979 0.09108 -0.0282 0.1091 1.0000
15.000 1.1456 0.10271 0.09379 -0.0284 0.1029 1.0000
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Polar data table (+)
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