GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 50,000 Max Cl/Cd: 33.26 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe526-il-50000-n5.txt Download as CSV file: xf-goe526-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 526 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 -0.3204 0.10460 0.09718 -0.0409 1.0000 0.0986
-9.000 -0.3273 0.10211 0.09479 -0.0399 1.0000 0.0968
-8.500 -0.3931 0.09640 0.08938 -0.0394 1.0000 0.0906
-8.250 -0.4074 0.09471 0.08778 -0.0368 1.0000 0.0904
-8.000 -0.4235 0.09308 0.08626 -0.0341 1.0000 0.0900
-7.750 -0.4381 0.09108 0.08432 -0.0320 1.0000 0.0897
-7.500 -0.4304 0.08660 0.07980 -0.0362 0.9934 0.0893
-7.250 -0.4189 0.08173 0.07487 -0.0410 0.9849 0.0887
-7.000 -0.4086 0.07683 0.06986 -0.0456 0.9763 0.0880
-6.750 -0.3973 0.07166 0.06455 -0.0503 0.9684 0.0876
-6.500 -0.3891 0.06658 0.05926 -0.0540 0.9595 0.0881
-6.250 -0.3805 0.06133 0.05370 -0.0572 0.9512 0.0893
-6.000 -0.3693 0.05615 0.04807 -0.0598 0.9435 0.0901
-5.750 -0.3575 0.05166 0.04308 -0.0609 0.9362 0.0906
-5.500 -0.3383 0.04949 0.04079 -0.0612 0.9296 0.0916
-5.250 -0.3117 0.04762 0.03877 -0.0626 0.9248 0.0935
-5.000 -0.2966 0.04588 0.03682 -0.0617 0.9171 0.0960
-4.750 -0.2743 0.04340 0.03392 -0.0623 0.9112 0.0990
-4.500 -0.2476 0.04057 0.03046 -0.0633 0.9066 0.1017
-4.250 -0.2316 0.03916 0.02881 -0.0619 0.8987 0.1040
-4.000 -0.2032 0.03825 0.02782 -0.0626 0.8934 0.1079
-3.750 -0.1754 0.03691 0.02614 -0.0630 0.8882 0.1127
-3.500 -0.1544 0.03564 0.02449 -0.0621 0.8806 0.1169
-3.250 -0.1225 0.03494 0.02378 -0.0631 0.8755 0.1225
-3.000 -0.0971 0.03408 0.02263 -0.0627 0.8686 0.1288
-2.750 -0.0688 0.03336 0.02182 -0.0629 0.8612 0.1354
-2.500 -0.0279 0.03247 0.02065 -0.0650 0.8562 0.1460
-2.250 -0.0077 0.03201 0.02024 -0.0637 0.8457 0.1533
-2.000 0.0345 0.03119 0.01928 -0.0659 0.8401 0.1667
-1.750 0.0600 0.03084 0.01885 -0.0653 0.8304 0.1792
-1.500 0.1007 0.03021 0.01819 -0.0673 0.8242 0.1961
-1.250 0.1324 0.02978 0.01776 -0.0678 0.8165 0.2134
-1.000 0.1635 0.02938 0.01738 -0.0682 0.8083 0.2335
-0.750 0.2060 0.02868 0.01679 -0.0704 0.8035 0.2614
-0.500 0.2229 0.02857 0.01679 -0.0685 0.7920 0.2845
-0.250 0.2609 0.02780 0.01628 -0.0698 0.7865 0.3315
0.000 0.2761 0.02740 0.01636 -0.0676 0.7752 0.4026
0.250 0.4000 0.02560 0.01587 -0.0844 0.7730 1.0000
0.500 0.4314 0.02556 0.01559 -0.0845 0.7651 1.0000
0.750 0.4521 0.02572 0.01560 -0.0829 0.7538 1.0000
1.000 0.4742 0.02588 0.01561 -0.0815 0.7432 1.0000
1.250 0.5039 0.02583 0.01542 -0.0813 0.7343 1.0000
1.500 0.5211 0.02611 0.01561 -0.0792 0.7220 1.0000
1.750 0.5567 0.02588 0.01525 -0.0797 0.7146 1.0000
2.000 0.5704 0.02626 0.01557 -0.0771 0.7011 1.0000
2.250 0.5918 0.02644 0.01568 -0.0757 0.6897 1.0000
2.500 0.6218 0.02636 0.01551 -0.0754 0.6805 1.0000
2.750 0.6371 0.02673 0.01584 -0.0730 0.6673 1.0000
3.000 0.6609 0.02686 0.01592 -0.0719 0.6566 1.0000
3.250 0.6868 0.02691 0.01592 -0.0710 0.6463 1.0000
3.500 0.7026 0.02732 0.01632 -0.0689 0.6335 1.0000
3.750 0.7288 0.02741 0.01636 -0.0681 0.6238 1.0000
4.000 0.7505 0.02764 0.01657 -0.0667 0.6128 1.0000
4.250 0.7673 0.02809 0.01703 -0.0648 0.6009 1.0000
4.500 0.8005 0.02795 0.01684 -0.0650 0.5931 1.0000
4.750 0.8130 0.02858 0.01749 -0.0625 0.5805 1.0000
5.000 0.8332 0.02892 0.01784 -0.0610 0.5697 1.0000
5.250 0.8636 0.02879 0.01768 -0.0607 0.5600 1.0000
5.500 0.8777 0.02929 0.01820 -0.0584 0.5470 1.0000
5.750 0.8972 0.02955 0.01846 -0.0566 0.5345 1.0000
6.000 0.9217 0.02953 0.01840 -0.0554 0.5221 1.0000
6.250 0.9468 0.02952 0.01835 -0.0543 0.5095 1.0000
6.500 0.9605 0.03005 0.01892 -0.0520 0.4963 1.0000
6.750 0.9789 0.03047 0.01936 -0.0503 0.4847 1.0000
7.000 1.0075 0.03055 0.01940 -0.0498 0.4745 1.0000
7.250 1.0193 0.03128 0.02023 -0.0475 0.4627 1.0000
7.500 1.0373 0.03180 0.02078 -0.0458 0.4514 1.0000
7.750 1.0639 0.03199 0.02094 -0.0451 0.4402 1.0000
8.000 1.0735 0.03281 0.02187 -0.0425 0.4280 1.0000
8.250 1.0874 0.03347 0.02260 -0.0404 0.4160 1.0000
8.500 1.1071 0.03390 0.02303 -0.0389 0.4036 1.0000
8.750 1.1201 0.03449 0.02365 -0.0366 0.3900 1.0000
9.000 1.1226 0.03545 0.02469 -0.0331 0.3760 1.0000
9.250 1.1276 0.03633 0.02562 -0.0301 0.3613 1.0000
9.500 1.1322 0.03723 0.02654 -0.0272 0.3461 1.0000
9.750 1.1366 0.03820 0.02753 -0.0244 0.3310 1.0000
10.000 1.1411 0.03924 0.02858 -0.0218 0.3161 1.0000
10.250 1.1465 0.04032 0.02966 -0.0195 0.3019 1.0000
10.500 1.1489 0.04172 0.03112 -0.0173 0.2878 1.0000
10.750 1.1501 0.04333 0.03280 -0.0152 0.2741 1.0000
11.000 1.1523 0.04497 0.03448 -0.0133 0.2610 1.0000
11.250 1.1552 0.04664 0.03616 -0.0116 0.2486 1.0000
11.500 1.1591 0.04826 0.03777 -0.0101 0.2371 1.0000
11.750 1.1634 0.04991 0.03938 -0.0087 0.2262 1.0000
12.000 1.1634 0.05216 0.04171 -0.0075 0.2153 1.0000
12.250 1.1664 0.05418 0.04374 -0.0063 0.2058 1.0000
12.500 1.1725 0.05583 0.04530 -0.0052 0.1967 1.0000
12.750 1.1712 0.05854 0.04813 -0.0044 0.1878 1.0000
13.000 1.1788 0.06025 0.04975 -0.0034 0.1798 1.0000
13.250 1.1775 0.06314 0.05279 -0.0029 0.1723 1.0000
13.500 1.1880 0.06467 0.05423 -0.0020 0.1649 1.0000
13.750 1.1811 0.06837 0.05817 -0.0018 0.1587 1.0000
14.000 1.1901 0.07020 0.05998 -0.0011 0.1524 1.0000
14.250 1.1875 0.07356 0.06348 -0.0010 0.1473 1.0000
14.500 1.1769 0.07800 0.06816 -0.0016 0.1426 1.0000
14.750 1.1826 0.08030 0.07049 -0.0013 0.1376 1.0000
15.000 1.1802 0.08390 0.07421 -0.0016 0.1337 1.0000
15.250 1.1529 0.09127 0.08190 -0.0040 0.1309 1.0000
15.500 1.1239 0.09951 0.09039 -0.0071 0.1281 1.0000
15.750 1.1100 0.10548 0.09649 -0.0093 0.1247 1.0000
16.000 1.1256 0.10619 0.09717 -0.0086 0.1211 1.0000
16.250 0.9717 0.14391 0.13518 -0.0297 0.1179 1.0000
16.500 0.9496 0.15435 0.14561 -0.0351 0.1138 1.0000
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