GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 500,000 Max Cl/Cd: 104.81 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe322-il-500000.txt Download as CSV file: xf-goe322-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1874 0.08642 0.08321 -0.0398 0.7156 0.0287
-7.750 -0.1817 0.08302 0.07980 -0.0425 0.7118 0.0297
-7.500 -0.1815 0.07512 0.07183 -0.0592 0.7085 0.0309
-7.250 -0.1740 0.07117 0.06791 -0.0599 0.7048 0.0312
-7.000 -0.1606 0.06866 0.06539 -0.0606 0.7007 0.0315
-6.750 -0.1455 0.06616 0.06286 -0.0620 0.6967 0.0318
-6.500 -0.1292 0.06342 0.06006 -0.0642 0.6930 0.0323
-6.250 -0.1112 0.06033 0.05692 -0.0672 0.6891 0.0329
-6.000 -0.0912 0.05680 0.05333 -0.0709 0.6848 0.0340
-5.750 -0.0643 0.04802 0.04423 -0.0803 0.6813 0.0369
-5.500 -0.0449 0.04623 0.04239 -0.0807 0.6773 0.0373
-5.250 -0.0235 0.04438 0.04048 -0.0815 0.6733 0.0379
-5.000 -0.0002 0.04220 0.03822 -0.0827 0.6687 0.0388
-4.750 0.0298 0.03561 0.03111 -0.0862 0.6650 0.0433
-4.500 0.0527 0.03403 0.02948 -0.0866 0.6606 0.0439
-4.250 0.0770 0.03272 0.02812 -0.0870 0.6555 0.0445
-4.000 0.1026 0.03126 0.02659 -0.0875 0.6495 0.0457
-3.750 0.1312 0.02767 0.02250 -0.0882 0.6445 0.0513
-3.500 0.1569 0.02656 0.02137 -0.0885 0.6386 0.0522
-3.250 0.1837 0.02548 0.02023 -0.0888 0.6326 0.0536
-3.000 0.2130 0.02336 0.01760 -0.0889 0.6280 0.0601
-2.750 0.2429 0.01791 0.01127 -0.0883 0.6240 0.0430
-2.500 0.2709 0.01595 0.00918 -0.0884 0.6186 0.0415
-2.250 0.2996 0.01479 0.00780 -0.0884 0.6136 0.0410
-2.000 0.3284 0.01389 0.00672 -0.0884 0.6089 0.0405
-1.750 0.3574 0.01321 0.00596 -0.0885 0.6031 0.0405
-1.500 0.3861 0.01271 0.00537 -0.0885 0.5976 0.0408
-1.250 0.4147 0.01232 0.00490 -0.0885 0.5927 0.0412
-1.000 0.4436 0.01197 0.00453 -0.0886 0.5870 0.0416
-0.750 0.4723 0.01170 0.00420 -0.0887 0.5816 0.0422
-0.500 0.5010 0.01148 0.00394 -0.0888 0.5763 0.0431
-0.250 0.5296 0.01114 0.00362 -0.0889 0.5702 0.0447
0.000 0.5583 0.01099 0.00344 -0.0890 0.5647 0.0461
0.250 0.5872 0.01088 0.00332 -0.0891 0.5592 0.0480
0.500 0.6161 0.01079 0.00321 -0.0893 0.5524 0.0502
0.750 0.6447 0.01072 0.00312 -0.0894 0.5456 0.0560
1.000 0.6735 0.01060 0.00308 -0.0896 0.5379 0.0769
1.250 0.7018 0.01050 0.00310 -0.0897 0.5311 0.1396
1.500 0.7304 0.01031 0.00313 -0.0900 0.5243 0.2122
1.750 0.7585 0.00854 0.00324 -0.0904 0.5175 1.0000
2.000 0.7867 0.00864 0.00327 -0.0904 0.5104 1.0000
2.250 0.8148 0.00875 0.00329 -0.0905 0.5027 1.0000
2.500 0.8428 0.00887 0.00334 -0.0906 0.4949 1.0000
2.750 0.8706 0.00900 0.00339 -0.0906 0.4858 1.0000
3.000 0.8986 0.00911 0.00345 -0.0907 0.4765 1.0000
3.250 0.9260 0.00928 0.00353 -0.0907 0.4670 1.0000
3.500 0.9539 0.00940 0.00362 -0.0908 0.4571 1.0000
3.750 0.9814 0.00957 0.00372 -0.0908 0.4474 1.0000
4.000 1.0085 0.00976 0.00384 -0.0908 0.4365 1.0000
4.250 1.0358 0.00993 0.00397 -0.0909 0.4249 1.0000
4.500 1.0626 0.01014 0.00412 -0.0909 0.4131 1.0000
4.750 1.0890 0.01039 0.00430 -0.0908 0.4011 1.0000
5.000 1.1150 0.01067 0.00450 -0.0907 0.3892 1.0000
5.250 1.1412 0.01092 0.00470 -0.0906 0.3778 1.0000
5.500 1.1670 0.01120 0.00493 -0.0905 0.3677 1.0000
5.750 1.1921 0.01153 0.00520 -0.0902 0.3580 1.0000
6.000 1.2179 0.01179 0.00544 -0.0901 0.3493 1.0000
6.250 1.2427 0.01213 0.00573 -0.0898 0.3413 1.0000
6.500 1.2680 0.01240 0.00600 -0.0897 0.3336 1.0000
6.750 1.2921 0.01276 0.00631 -0.0893 0.3255 1.0000
7.000 1.3163 0.01309 0.00662 -0.0890 0.3158 1.0000
7.250 1.3401 0.01344 0.00694 -0.0886 0.3068 1.0000
7.500 1.3629 0.01383 0.00730 -0.0881 0.2978 1.0000
7.750 1.3865 0.01416 0.00762 -0.0877 0.2883 1.0000
8.000 1.4082 0.01460 0.00802 -0.0871 0.2789 1.0000
8.250 1.4306 0.01497 0.00839 -0.0865 0.2696 1.0000
8.500 1.4517 0.01539 0.00880 -0.0858 0.2600 1.0000
8.750 1.4708 0.01592 0.00927 -0.0848 0.2491 1.0000
9.000 1.4892 0.01644 0.00977 -0.0837 0.2375 1.0000
9.250 1.5062 0.01701 0.01031 -0.0824 0.2258 1.0000
9.500 1.5192 0.01767 0.01093 -0.0805 0.2149 1.0000
9.750 1.5290 0.01847 0.01169 -0.0781 0.2050 1.0000
10.000 1.5390 0.01936 0.01256 -0.0761 0.1950 1.0000
10.250 1.5490 0.02035 0.01354 -0.0744 0.1859 1.0000
10.500 1.5569 0.02159 0.01475 -0.0727 0.1771 1.0000
10.750 1.5658 0.02289 0.01604 -0.0714 0.1686 1.0000
11.000 1.5737 0.02439 0.01752 -0.0702 0.1590 1.0000
11.250 1.5798 0.02614 0.01925 -0.0692 0.1494 1.0000
11.500 1.5846 0.02804 0.02112 -0.0682 0.1372 1.0000
11.750 1.5842 0.03046 0.02343 -0.0670 0.1161 1.0000
12.000 1.5584 0.03521 0.02790 -0.0647 0.0742 1.0000
12.250 1.5311 0.04026 0.03284 -0.0626 0.0439 1.0000
12.500 1.5122 0.04466 0.03719 -0.0612 0.0227 1.0000
12.750 1.5090 0.04761 0.04020 -0.0604 0.0204 1.0000
13.000 1.5086 0.05038 0.04305 -0.0599 0.0191 1.0000
13.250 1.5087 0.05317 0.04594 -0.0595 0.0184 1.0000
13.500 1.5078 0.05617 0.04906 -0.0592 0.0178 1.0000
13.750 1.5054 0.05944 0.05244 -0.0590 0.0173 1.0000
14.000 1.5012 0.06302 0.05612 -0.0589 0.0169 1.0000
14.250 1.4952 0.06688 0.06010 -0.0590 0.0165 1.0000
14.500 1.4871 0.07113 0.06447 -0.0591 0.0162 1.0000
14.750 1.4791 0.07547 0.06892 -0.0595 0.0159 1.0000
15.000 1.4730 0.07957 0.07314 -0.0599 0.0158 1.0000
15.250 1.4654 0.08397 0.07765 -0.0604 0.0156 1.0000
15.500 1.4568 0.08861 0.08241 -0.0611 0.0154 1.0000
15.750 1.4471 0.09347 0.08739 -0.0619 0.0152 1.0000
16.000 1.4361 0.09858 0.09262 -0.0629 0.0150 1.0000
16.250 1.4245 0.10389 0.09805 -0.0641 0.0148 1.0000
16.500 1.4128 0.10931 0.10358 -0.0654 0.0146 1.0000
16.750 1.4008 0.11484 0.10922 -0.0668 0.0145 1.0000
17.000 1.3887 0.12043 0.11493 -0.0685 0.0143 1.0000
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Polar data table (+)
Polar graphs
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