GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 29B AIRFOIL (goe29b-il) Reynolds number: 500,000 Max Cl/Cd: 99.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe29b-il-500000.txt Download as CSV file: xf-goe29b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 29B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1919 0.09780 0.09555 -0.0258 0.9095 0.0287
-8.000 -0.1863 0.09526 0.09292 -0.0277 0.8870 0.0298
-7.750 -0.1846 0.09296 0.09054 -0.0325 0.8651 0.0300
-7.500 -0.1774 0.08982 0.08734 -0.0348 0.8471 0.0301
-7.250 -0.1663 0.08668 0.08414 -0.0333 0.8300 0.0303
-7.000 -0.1546 0.08405 0.08144 -0.0337 0.8106 0.0304
-6.750 -0.1417 0.08154 0.07885 -0.0350 0.7895 0.0307
-6.500 -0.1274 0.07903 0.07625 -0.0371 0.7674 0.0310
-6.250 -0.1116 0.07645 0.07357 -0.0397 0.7456 0.0315
-6.000 -0.0941 0.07374 0.07076 -0.0429 0.7250 0.0322
-5.750 -0.0737 0.07079 0.06771 -0.0471 0.7068 0.0334
-5.500 -0.0302 0.06548 0.06220 -0.0639 0.6921 0.0344
-5.250 -0.0171 0.06283 0.05949 -0.0626 0.6779 0.0346
-5.000 0.0006 0.06042 0.05701 -0.0633 0.6651 0.0348
-4.750 0.0220 0.05807 0.05459 -0.0652 0.6537 0.0352
-4.500 0.0461 0.05570 0.05212 -0.0679 0.6433 0.0357
-4.250 0.0730 0.05316 0.04952 -0.0713 0.6348 0.0365
-4.000 0.1328 0.04872 0.04474 -0.0845 0.6266 0.0390
-3.750 0.1527 0.04562 0.04161 -0.0855 0.6188 0.0393
-3.500 0.1740 0.04359 0.03955 -0.0860 0.6104 0.0396
-3.250 0.1989 0.04170 0.03759 -0.0873 0.6026 0.0400
-3.000 0.2268 0.03978 0.03560 -0.0891 0.5942 0.0408
-2.750 0.2571 0.03777 0.03347 -0.0913 0.5862 0.0420
-2.500 0.3074 0.03388 0.02919 -0.0972 0.5780 0.0445
-2.250 0.3308 0.03215 0.02742 -0.0978 0.5699 0.0449
-2.000 0.3567 0.03079 0.02603 -0.0984 0.5611 0.0455
-1.750 0.3849 0.02944 0.02457 -0.0993 0.5527 0.0465
-1.500 0.4287 0.02747 0.02217 -0.1014 0.5440 0.0503
-1.250 0.4558 0.02492 0.01950 -0.1026 0.5352 0.0508
-1.000 0.4827 0.02378 0.01833 -0.1031 0.5243 0.0514
-0.750 0.5107 0.02282 0.01727 -0.1036 0.5145 0.0523
-0.500 0.5402 0.02179 0.01611 -0.1040 0.5054 0.0541
-0.250 0.5753 0.01981 0.01371 -0.1047 0.4979 0.0579
0.000 0.6094 0.01647 0.00982 -0.1052 0.4904 0.0502
0.250 0.6393 0.01494 0.00795 -0.1054 0.4826 0.0504
0.500 0.6670 0.01469 0.00775 -0.1056 0.4742 0.0519
0.750 0.6951 0.01451 0.00748 -0.1056 0.4668 0.0539
1.000 0.7246 0.01364 0.00640 -0.1056 0.4600 0.0553
1.250 0.7534 0.01324 0.00573 -0.1054 0.4536 0.0572
1.500 0.7816 0.01283 0.00534 -0.1054 0.4476 0.0594
1.750 0.8096 0.01276 0.00525 -0.1054 0.4411 0.0622
2.000 0.8377 0.01270 0.00504 -0.1052 0.4349 0.0647
2.250 0.8660 0.01228 0.00464 -0.1052 0.4288 0.0673
2.500 0.8937 0.01227 0.00462 -0.1051 0.4221 0.0705
2.750 0.9216 0.01224 0.00455 -0.1049 0.4152 0.0733
3.000 0.9494 0.01203 0.00432 -0.1048 0.4069 0.0760
3.250 0.9770 0.01200 0.00430 -0.1047 0.3981 0.0794
3.500 1.0045 0.01200 0.00427 -0.1046 0.3875 0.0822
3.750 1.0321 0.01204 0.00429 -0.1044 0.3760 0.0847
4.000 1.0595 0.01196 0.00420 -0.1044 0.3625 0.0885
4.250 1.0866 0.01205 0.00425 -0.1042 0.3448 0.0918
4.500 1.1128 0.01227 0.00436 -0.1039 0.3207 0.0954
4.750 1.1384 0.01255 0.00450 -0.1037 0.2946 0.1000
5.000 1.1638 0.01288 0.00473 -0.1033 0.2778 0.1055
5.250 1.1895 0.01317 0.00498 -0.1030 0.2675 0.1131
5.500 1.2149 0.01347 0.00528 -0.1027 0.2597 0.1380
5.750 1.2375 0.01245 0.00565 -0.1020 0.2549 1.0000
6.000 1.2633 0.01275 0.00590 -0.1016 0.2505 1.0000
6.250 1.2883 0.01311 0.00621 -0.1012 0.2461 1.0000
6.500 1.3130 0.01350 0.00655 -0.1008 0.2418 1.0000
6.750 1.3389 0.01374 0.00680 -0.1005 0.2390 1.0000
7.000 1.3642 0.01403 0.00711 -0.1001 0.2363 1.0000
7.250 1.3890 0.01436 0.00743 -0.0997 0.2336 1.0000
7.500 1.4131 0.01474 0.00779 -0.0992 0.2308 1.0000
7.750 1.4360 0.01523 0.00824 -0.0985 0.2272 1.0000
8.000 1.4609 0.01549 0.00855 -0.0981 0.2244 1.0000
8.250 1.4857 0.01575 0.00885 -0.0977 0.2210 1.0000
8.500 1.5094 0.01609 0.00920 -0.0972 0.2173 1.0000
8.750 1.5316 0.01654 0.00964 -0.0965 0.2136 1.0000
9.000 1.5533 0.01703 0.01013 -0.0957 0.2099 1.0000
9.250 1.5777 0.01725 0.01042 -0.0953 0.2072 1.0000
9.500 1.6010 0.01754 0.01076 -0.0948 0.2038 1.0000
9.750 1.6227 0.01794 0.01116 -0.0940 0.1995 1.0000
10.000 1.6416 0.01853 0.01173 -0.0929 0.1948 1.0000
10.250 1.6657 0.01869 0.01199 -0.0925 0.1911 1.0000
10.500 1.6873 0.01902 0.01236 -0.0917 0.1858 1.0000
10.750 1.7052 0.01958 0.01289 -0.0905 0.1802 1.0000
11.000 1.7271 0.01984 0.01323 -0.0898 0.1745 1.0000
11.250 1.7430 0.02037 0.01374 -0.0883 0.1664 1.0000
11.500 1.7587 0.02090 0.01428 -0.0868 0.1552 1.0000
11.750 1.7689 0.02180 0.01509 -0.0847 0.1417 1.0000
12.000 1.7755 0.02300 0.01623 -0.0825 0.1301 1.0000
12.250 1.7811 0.02435 0.01756 -0.0804 0.1214 1.0000
12.500 1.7848 0.02596 0.01916 -0.0785 0.1137 1.0000
12.750 1.7872 0.02780 0.02100 -0.0767 0.1057 1.0000
13.000 1.7908 0.02964 0.02286 -0.0753 0.0977 1.0000
13.250 1.7908 0.03193 0.02514 -0.0739 0.0880 1.0000
13.500 1.7789 0.03552 0.02862 -0.0725 0.0668 1.0000
13.750 1.7514 0.04108 0.03405 -0.0714 0.0418 1.0000
14.000 1.7275 0.04669 0.03967 -0.0710 0.0275 1.0000
14.250 1.7141 0.05123 0.04429 -0.0709 0.0237 1.0000
14.500 1.7040 0.05543 0.04859 -0.0710 0.0218 1.0000
14.750 1.6961 0.05942 0.05270 -0.0711 0.0209 1.0000
15.000 1.6870 0.06371 0.05711 -0.0714 0.0202 1.0000
15.250 1.6764 0.06830 0.06181 -0.0718 0.0196 1.0000
15.500 1.6646 0.07316 0.06681 -0.0725 0.0191 1.0000
15.750 1.6515 0.07835 0.07213 -0.0734 0.0187 1.0000
16.250 1.6254 0.08903 0.08306 -0.0756 0.0182 1.0000
16.500 1.6130 0.09441 0.08858 -0.0768 0.0180 1.0000
16.750 1.5996 0.10000 0.09430 -0.0782 0.0178 1.0000
17.000 1.5852 0.10582 0.10025 -0.0798 0.0176 1.0000
17.250 1.5701 0.11188 0.10644 -0.0816 0.0175 1.0000
17.500 1.5550 0.11804 0.11273 -0.0836 0.0173 1.0000
17.750 1.5395 0.12434 0.11915 -0.0858 0.0172 1.0000
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