GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 100,000 Max Cl/Cd: 50.17 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe534-il-100000-n5.txt Download as CSV file: xf-goe534-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2718 0.09600 0.09066 -0.0350 1.0000 0.0584
-9.500 -0.2770 0.09196 0.08668 -0.0364 1.0000 0.0590
-9.250 -0.2847 0.08772 0.08251 -0.0376 1.0000 0.0593
-9.000 -0.2968 0.08319 0.07806 -0.0389 1.0000 0.0596
-8.750 -0.3203 0.07785 0.07284 -0.0401 1.0000 0.0600
-8.500 -0.3465 0.07410 0.06925 -0.0393 1.0000 0.0603
-8.250 -0.3260 0.07138 0.06655 -0.0433 0.9857 0.0613
-8.000 -0.3691 0.03523 0.02900 -0.0926 0.9405 0.0674
-7.750 -0.3374 0.03307 0.02661 -0.0957 0.9272 0.0699
-7.500 -0.3073 0.02964 0.02256 -0.0995 0.9139 0.0739
-7.250 -0.2725 0.02871 0.02158 -0.1012 0.9019 0.0771
-7.000 -0.2421 0.02690 0.01933 -0.1029 0.8873 0.0821
-6.750 -0.2095 0.02616 0.01856 -0.1039 0.8736 0.0858
-6.500 -0.1774 0.02482 0.01680 -0.1051 0.8605 0.0908
-6.250 -0.1475 0.02425 0.01625 -0.1054 0.8456 0.0943
-6.000 -0.1182 0.02347 0.01517 -0.1056 0.8307 0.0990
-5.750 -0.0891 0.02285 0.01447 -0.1057 0.8166 0.1027
-5.500 -0.0601 0.02241 0.01391 -0.1056 0.8025 0.1070
-5.250 -0.0331 0.02194 0.01324 -0.1053 0.7872 0.1125
-5.000 -0.0057 0.02167 0.01297 -0.1049 0.7729 0.1175
-4.750 0.0224 0.02125 0.01227 -0.1046 0.7592 0.1224
-4.500 0.0487 0.02073 0.01169 -0.1039 0.7441 0.1251
-4.250 0.0753 0.02029 0.01120 -0.1033 0.7296 0.1273
-4.000 0.1024 0.01989 0.01068 -0.1027 0.7160 0.1293
-3.750 0.1289 0.01953 0.01021 -0.1020 0.7011 0.1319
-3.500 0.1554 0.01920 0.00976 -0.1013 0.6861 0.1347
-3.250 0.1821 0.01890 0.00934 -0.1006 0.6720 0.1371
-3.000 0.2084 0.01860 0.00899 -0.0998 0.6580 0.1395
-2.750 0.2345 0.01835 0.00872 -0.0991 0.6427 0.1424
-2.500 0.2609 0.01814 0.00844 -0.0984 0.6284 0.1461
-2.250 0.2875 0.01796 0.00814 -0.0977 0.6148 0.1507
-2.000 0.3138 0.01777 0.00794 -0.0970 0.6013 0.1566
-1.750 0.3403 0.01763 0.00774 -0.0963 0.5878 0.1650
-1.500 0.3667 0.01748 0.00759 -0.0956 0.5753 0.1763
-1.250 0.3931 0.01735 0.00745 -0.0950 0.5632 0.1945
-1.000 0.4198 0.01728 0.00741 -0.0944 0.5507 0.2214
-0.750 0.4465 0.01728 0.00739 -0.0938 0.5396 0.2533
-0.500 0.4731 0.01734 0.00747 -0.0932 0.5278 0.2825
-0.250 0.4997 0.01745 0.00754 -0.0926 0.5173 0.3086
0.000 0.5261 0.01758 0.00762 -0.0919 0.5069 0.3307
0.250 0.5524 0.01772 0.00773 -0.0912 0.4973 0.3501
0.500 0.5785 0.01788 0.00786 -0.0905 0.4874 0.3700
0.750 0.6046 0.01806 0.00801 -0.0898 0.4785 0.3925
1.000 0.6306 0.01823 0.00818 -0.0891 0.4689 0.4138
1.250 0.6570 0.01842 0.00831 -0.0885 0.4605 0.4329
1.500 0.6832 0.01858 0.00850 -0.0878 0.4509 0.4522
1.750 0.7097 0.01876 0.00859 -0.0872 0.4429 0.4710
2.000 0.7360 0.01889 0.00879 -0.0867 0.4330 0.4888
2.250 0.7624 0.01903 0.00888 -0.0861 0.4249 0.5055
2.500 0.7887 0.01917 0.00906 -0.0856 0.4156 0.5218
2.750 0.8149 0.01931 0.00918 -0.0850 0.4072 0.5388
3.000 0.8407 0.01945 0.00937 -0.0844 0.3984 0.5578
3.250 0.8662 0.01957 0.00952 -0.0838 0.3896 0.5800
3.500 0.8914 0.01969 0.00971 -0.0831 0.3813 0.6093
3.750 0.9155 0.01967 0.00990 -0.0822 0.3726 0.6611
4.000 0.9512 0.01951 0.01008 -0.0836 0.3637 1.0000
4.250 0.9759 0.01985 0.01034 -0.0829 0.3548 1.0000
4.500 1.0002 0.02022 0.01058 -0.0821 0.3474 1.0000
4.750 1.0242 0.02060 0.01093 -0.0813 0.3388 1.0000
5.000 1.0479 0.02099 0.01118 -0.0805 0.3320 1.0000
5.250 1.0712 0.02140 0.01160 -0.0796 0.3238 1.0000
5.500 1.0941 0.02181 0.01193 -0.0787 0.3167 1.0000
5.750 1.1169 0.02227 0.01235 -0.0778 0.3097 1.0000
6.000 1.1392 0.02272 0.01278 -0.0768 0.3026 1.0000
6.250 1.1613 0.02319 0.01312 -0.0758 0.2968 1.0000
6.500 1.1829 0.02370 0.01370 -0.0748 0.2898 1.0000
6.750 1.2041 0.02420 0.01416 -0.0737 0.2837 1.0000
7.000 1.2251 0.02474 0.01463 -0.0727 0.2783 1.0000
7.250 1.2453 0.02530 0.01526 -0.0715 0.2720 1.0000
7.500 1.2652 0.02586 0.01579 -0.0703 0.2665 1.0000
7.750 1.2853 0.02645 0.01629 -0.0692 0.2619 1.0000
8.000 1.3037 0.02709 0.01705 -0.0678 0.2562 1.0000
8.250 1.3219 0.02772 0.01769 -0.0665 0.2511 1.0000
8.500 1.3403 0.02835 0.01825 -0.0652 0.2468 1.0000
8.750 1.3570 0.02908 0.01905 -0.0637 0.2421 1.0000
9.000 1.3724 0.02981 0.01986 -0.0621 0.2372 1.0000
9.250 1.3877 0.03052 0.02058 -0.0605 0.2329 1.0000
9.500 1.4039 0.03123 0.02121 -0.0590 0.2291 1.0000
9.750 1.4138 0.03213 0.02225 -0.0568 0.2248 1.0000
10.000 1.4239 0.03301 0.02322 -0.0547 0.2205 1.0000
10.250 1.4346 0.03388 0.02411 -0.0528 0.2166 1.0000
10.500 1.4483 0.03472 0.02488 -0.0512 0.2131 1.0000
10.750 1.4543 0.03593 0.02625 -0.0492 0.2093 1.0000
11.000 1.4602 0.03718 0.02762 -0.0473 0.2052 1.0000
11.250 1.4674 0.03839 0.02889 -0.0457 0.2015 1.0000
11.500 1.4772 0.03950 0.02998 -0.0443 0.1982 1.0000
11.750 1.4818 0.04106 0.03164 -0.0429 0.1948 1.0000
12.000 1.4820 0.04297 0.03373 -0.0415 0.1910 1.0000
12.250 1.4844 0.04479 0.03564 -0.0404 0.1875 1.0000
12.500 1.4895 0.04644 0.03731 -0.0394 0.1842 1.0000
12.750 1.4960 0.04809 0.03896 -0.0386 0.1812 1.0000
13.000 1.4884 0.05112 0.04223 -0.0381 0.1778 1.0000
13.250 1.4835 0.05401 0.04527 -0.0377 0.1744 1.0000
13.500 1.4830 0.05653 0.04786 -0.0375 0.1713 1.0000
13.750 1.4883 0.05846 0.04979 -0.0372 0.1686 1.0000
14.000 1.4798 0.06212 0.05360 -0.0375 0.1657 1.0000
14.250 1.4619 0.06714 0.05886 -0.0385 0.1626 1.0000
14.500 1.4493 0.07170 0.06357 -0.0396 0.1595 1.0000
14.750 1.4467 0.07499 0.06692 -0.0403 0.1568 1.0000
15.000 1.4571 0.07648 0.06836 -0.0401 0.1544 1.0000
15.250 1.4121 0.08647 0.07870 -0.0442 0.1513 1.0000
15.500 1.3310 0.10355 0.09618 -0.0526 0.1468 1.0000
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