GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 100,000 Max Cl/Cd: 54.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe533-il-100000-n5.txt Download as CSV file: xf-goe533-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2571 0.10002 0.09523 -0.0415 1.0000 0.0809
-9.000 -0.2591 0.09764 0.09294 -0.0410 1.0000 0.0817
-8.750 -0.2837 0.08733 0.08267 -0.0503 0.9906 0.0574
-8.500 -0.2665 0.08273 0.07806 -0.0552 0.9769 0.0570
-8.000 -0.2717 0.05915 0.05415 -0.0861 0.9298 0.0496
-7.750 -0.2558 0.05412 0.04895 -0.0917 0.9118 0.0492
-7.500 -0.2409 0.04892 0.04345 -0.0970 0.8932 0.0489
-7.250 -0.2265 0.04364 0.03767 -0.1014 0.8745 0.0490
-7.000 -0.2096 0.03917 0.03249 -0.1044 0.8567 0.0496
-6.750 -0.1866 0.03652 0.02959 -0.1057 0.8407 0.0502
-6.500 -0.1631 0.03395 0.02663 -0.1066 0.8253 0.0504
-6.250 -0.1384 0.03171 0.02399 -0.1073 0.8111 0.0506
-6.000 -0.1127 0.02985 0.02178 -0.1077 0.7978 0.0509
-5.750 -0.0877 0.02827 0.01989 -0.1078 0.7843 0.0513
-5.500 -0.0618 0.02696 0.01832 -0.1078 0.7721 0.0520
-5.250 -0.0350 0.02588 0.01700 -0.1078 0.7613 0.0535
-5.000 -0.0088 0.02481 0.01565 -0.1077 0.7501 0.0547
-4.750 0.0180 0.02377 0.01435 -0.1075 0.7402 0.0556
-4.500 0.0449 0.02283 0.01317 -0.1072 0.7307 0.0563
-4.250 0.0716 0.02203 0.01217 -0.1068 0.7213 0.0571
-4.000 0.0986 0.02133 0.01130 -0.1064 0.7128 0.0579
-3.750 0.1244 0.02062 0.01059 -0.1061 0.7040 0.0590
-3.500 0.1507 0.02011 0.01005 -0.1057 0.6957 0.0611
-3.250 0.1769 0.01969 0.00958 -0.1053 0.6877 0.0636
-3.000 0.2031 0.01929 0.00909 -0.1049 0.6795 0.0660
-2.750 0.2295 0.01889 0.00863 -0.1045 0.6722 0.0682
-2.500 0.2555 0.01858 0.00830 -0.1041 0.6638 0.0711
-2.250 0.2828 0.01832 0.00792 -0.1038 0.6571 0.0753
-2.000 0.3089 0.01808 0.00770 -0.1035 0.6488 0.0825
-1.750 0.3359 0.01781 0.00741 -0.1033 0.6416 0.0977
-1.500 0.3624 0.01739 0.00712 -0.1031 0.6345 0.1377
-1.250 0.3872 0.01648 0.00701 -0.1032 0.6270 0.3358
-1.000 0.4119 0.01622 0.00716 -0.1023 0.6209 0.5054
-0.750 0.4351 0.01619 0.00740 -0.1011 0.6129 0.5832
-0.500 0.4585 0.01627 0.00759 -0.0996 0.6060 0.6553
-0.250 0.4817 0.01633 0.00770 -0.0981 0.5993 0.7070
0.000 0.5054 0.01633 0.00773 -0.0968 0.5916 0.7407
0.250 0.5308 0.01631 0.00765 -0.0959 0.5855 0.7671
0.500 0.5552 0.01630 0.00768 -0.0950 0.5778 0.7922
0.750 0.5807 0.01626 0.00763 -0.0942 0.5707 0.8175
1.250 0.6407 0.01615 0.00759 -0.0946 0.5556 0.9073
1.500 0.6765 0.01624 0.00751 -0.0962 0.5495 1.0000
1.750 0.7033 0.01646 0.00769 -0.0963 0.5411 1.0000
2.000 0.7311 0.01664 0.00773 -0.0963 0.5344 1.0000
2.250 0.7578 0.01687 0.00788 -0.0963 0.5270 1.0000
2.500 0.7846 0.01707 0.00800 -0.0961 0.5196 1.0000
2.750 0.8117 0.01729 0.00811 -0.0960 0.5134 1.0000
3.000 0.8375 0.01755 0.00835 -0.0958 0.5059 1.0000
3.250 0.8644 0.01774 0.00844 -0.0956 0.4996 1.0000
3.500 0.8897 0.01801 0.00870 -0.0952 0.4915 1.0000
3.750 0.9157 0.01822 0.00882 -0.0948 0.4844 1.0000
4.000 0.9409 0.01849 0.00907 -0.0944 0.4768 1.0000
4.250 0.9663 0.01874 0.00928 -0.0940 0.4694 1.0000
4.500 0.9916 0.01901 0.00950 -0.0936 0.4626 1.0000
4.750 1.0160 0.01931 0.00980 -0.0931 0.4547 1.0000
5.000 1.0414 0.01956 0.00997 -0.0927 0.4481 1.0000
5.250 1.0649 0.01991 0.01037 -0.0920 0.4402 1.0000
5.500 1.0900 0.02020 0.01060 -0.0916 0.4340 1.0000
5.750 1.1131 0.02057 0.01102 -0.0909 0.4264 1.0000
6.000 1.1369 0.02090 0.01133 -0.0903 0.4194 1.0000
6.250 1.1607 0.02127 0.01171 -0.0897 0.4133 1.0000
6.500 1.1833 0.02169 0.01219 -0.0890 0.4067 1.0000
6.750 1.2074 0.02205 0.01254 -0.0885 0.4013 1.0000
7.000 1.2297 0.02251 0.01308 -0.0877 0.3953 1.0000
7.250 1.2516 0.02297 0.01360 -0.0870 0.3891 1.0000
7.500 1.2751 0.02335 0.01396 -0.0864 0.3838 1.0000
7.750 1.2951 0.02388 0.01463 -0.0853 0.3772 1.0000
8.000 1.3158 0.02435 0.01516 -0.0844 0.3708 1.0000
8.250 1.3377 0.02480 0.01560 -0.0836 0.3651 1.0000
8.500 1.3548 0.02538 0.01633 -0.0822 0.3577 1.0000
8.750 1.3747 0.02582 0.01679 -0.0811 0.3510 1.0000
9.000 1.3900 0.02643 0.01752 -0.0795 0.3432 1.0000
9.250 1.4060 0.02694 0.01807 -0.0779 0.3353 1.0000
9.500 1.4188 0.02759 0.01881 -0.0759 0.3270 1.0000
9.750 1.4307 0.02818 0.01947 -0.0738 0.3192 1.0000
10.000 1.4402 0.02891 0.02028 -0.0715 0.3116 1.0000
10.250 1.4488 0.02968 0.02113 -0.0691 0.3038 1.0000
10.500 1.4570 0.03054 0.02206 -0.0668 0.2964 1.0000
10.750 1.4631 0.03154 0.02318 -0.0646 0.2887 1.0000
11.000 1.4707 0.03256 0.02426 -0.0626 0.2821 1.0000
11.250 1.4749 0.03385 0.02569 -0.0606 0.2747 1.0000
11.500 1.4809 0.03507 0.02694 -0.0588 0.2682 1.0000
11.750 1.4816 0.03676 0.02879 -0.0571 0.2602 1.0000
12.000 1.4841 0.03838 0.03044 -0.0555 0.2531 1.0000
12.250 1.4829 0.04047 0.03269 -0.0542 0.2452 1.0000
12.500 1.4847 0.04240 0.03466 -0.0531 0.2391 1.0000
12.750 1.4834 0.04481 0.03724 -0.0522 0.2324 1.0000
13.000 1.4838 0.04707 0.03953 -0.0515 0.2264 1.0000
13.250 1.4802 0.04994 0.04255 -0.0510 0.2198 1.0000
13.500 1.4772 0.05274 0.04541 -0.0506 0.2132 1.0000
13.750 1.4711 0.05607 0.04887 -0.0505 0.2063 1.0000
14.000 1.4662 0.05930 0.05215 -0.0505 0.1998 1.0000
14.250 1.4608 0.06277 0.05573 -0.0506 0.1938 1.0000
14.500 1.4542 0.06648 0.05953 -0.0509 0.1876 1.0000
14.750 1.4503 0.06987 0.06295 -0.0512 0.1816 1.0000
15.000 1.4402 0.07439 0.06763 -0.0521 0.1751 1.0000
15.250 1.4369 0.07780 0.07101 -0.0525 0.1684 1.0000
15.500 1.4233 0.08320 0.07662 -0.0540 0.1615 1.0000
15.750 1.4161 0.08748 0.08090 -0.0551 0.1539 1.0000
16.000 1.4005 0.09356 0.08718 -0.0571 0.1462 1.0000
16.250 1.3899 0.09873 0.09238 -0.0589 0.1379 1.0000
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Polar data table (+)
Polar graphs
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