GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 200,000 Max Cl/Cd: 75.17 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe322-il-200000.txt Download as CSV file: xf-goe322-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1854 0.10210 0.09835 -0.0392 0.8183 0.0473
-8.750 -0.1824 0.09935 0.09558 -0.0426 0.8117 0.0494
-8.500 -0.1923 0.09686 0.09308 -0.0520 0.8052 0.0502
-8.250 -0.1841 0.09252 0.08876 -0.0525 0.7991 0.0506
-8.000 -0.1680 0.08936 0.08555 -0.0495 0.7936 0.0512
-7.750 -0.1566 0.08666 0.08282 -0.0493 0.7882 0.0521
-7.500 -0.1473 0.08393 0.08009 -0.0506 0.7821 0.0532
-7.250 -0.1415 0.08129 0.07742 -0.0524 0.7768 0.0546
-7.000 -0.1317 0.07807 0.07417 -0.0569 0.7716 0.0566
-6.750 -0.1165 0.07206 0.06799 -0.0744 0.7656 0.0593
-6.500 -0.1054 0.06926 0.06521 -0.0714 0.7605 0.0600
-6.250 -0.0915 0.06688 0.06281 -0.0706 0.7556 0.0610
-6.000 -0.0750 0.06423 0.06015 -0.0720 0.7497 0.0624
-5.750 -0.0565 0.06130 0.05713 -0.0747 0.7448 0.0647
-5.500 -0.0251 0.05644 0.05174 -0.0852 0.7408 0.0697
-5.250 -0.0092 0.05324 0.04865 -0.0849 0.7347 0.0705
-5.000 0.0089 0.05096 0.04636 -0.0848 0.7294 0.0717
-4.750 0.0294 0.04890 0.04420 -0.0852 0.7252 0.0740
-4.500 0.0640 0.04628 0.04100 -0.0899 0.7198 0.0818
-4.250 0.0829 0.04303 0.03784 -0.0901 0.7144 0.0830
-4.000 0.1046 0.04098 0.03575 -0.0902 0.7100 0.0847
-3.750 0.1289 0.03919 0.03387 -0.0907 0.7049 0.0877
-3.500 0.1601 0.03709 0.03127 -0.0924 0.6992 0.0961
-3.250 0.1830 0.03487 0.02905 -0.0925 0.6942 0.0980
-3.000 0.2082 0.03334 0.02745 -0.0926 0.6881 0.1015
-2.750 0.2368 0.03173 0.02550 -0.0932 0.6812 0.1118
-2.500 0.2620 0.03022 0.02393 -0.0931 0.6762 0.1161
-2.250 0.2905 0.02897 0.02243 -0.0935 0.6702 0.1275
-2.000 0.3298 0.02340 0.01565 -0.0926 0.6656 0.0682
-1.750 0.3582 0.02177 0.01379 -0.0925 0.6611 0.0662
-1.500 0.3870 0.02061 0.01238 -0.0924 0.6564 0.0652
-1.250 0.4157 0.01987 0.01150 -0.0923 0.6501 0.0665
-1.000 0.4445 0.01913 0.01058 -0.0921 0.6453 0.0673
-0.750 0.4732 0.01847 0.00977 -0.0920 0.6409 0.0679
-0.500 0.5014 0.01799 0.00925 -0.0919 0.6343 0.0688
-0.250 0.5294 0.01724 0.00849 -0.0917 0.6292 0.0708
0.000 0.5575 0.01681 0.00806 -0.0916 0.6245 0.0742
0.250 0.5853 0.01656 0.00784 -0.0915 0.6178 0.0800
0.500 0.6134 0.01612 0.00742 -0.0914 0.6127 0.0896
0.750 0.6415 0.01572 0.00713 -0.0913 0.6073 0.1200
1.000 0.6680 0.01493 0.00697 -0.0914 0.6005 0.3075
1.250 0.7008 0.01327 0.00675 -0.0918 0.5953 1.0000
1.500 0.7281 0.01339 0.00678 -0.0917 0.5882 1.0000
1.750 0.7561 0.01343 0.00667 -0.0915 0.5819 1.0000
2.000 0.7837 0.01349 0.00661 -0.0914 0.5750 1.0000
2.250 0.8112 0.01353 0.00655 -0.0913 0.5668 1.0000
2.500 0.8387 0.01359 0.00650 -0.0911 0.5590 1.0000
2.750 0.8660 0.01364 0.00645 -0.0909 0.5501 1.0000
3.000 0.8930 0.01373 0.00647 -0.0908 0.5412 1.0000
3.250 0.9203 0.01379 0.00640 -0.0906 0.5323 1.0000
3.500 0.9468 0.01392 0.00650 -0.0904 0.5219 1.0000
3.750 0.9738 0.01404 0.00651 -0.0902 0.5131 1.0000
4.000 1.0001 0.01419 0.00663 -0.0900 0.5029 1.0000
4.250 1.0265 0.01438 0.00677 -0.0899 0.4934 1.0000
4.500 1.0529 0.01456 0.00685 -0.0897 0.4842 1.0000
4.750 1.0786 0.01476 0.00707 -0.0894 0.4734 1.0000
5.000 1.1043 0.01498 0.00722 -0.0892 0.4635 1.0000
5.250 1.1297 0.01520 0.00738 -0.0889 0.4531 1.0000
5.500 1.1547 0.01545 0.00764 -0.0885 0.4421 1.0000
5.750 1.1796 0.01573 0.00786 -0.0882 0.4321 1.0000
6.000 1.2041 0.01602 0.00810 -0.0878 0.4220 1.0000
6.250 1.2282 0.01634 0.00843 -0.0874 0.4118 1.0000
6.500 1.2521 0.01670 0.00872 -0.0870 0.4028 1.0000
6.750 1.2754 0.01705 0.00908 -0.0865 0.3930 1.0000
7.000 1.2985 0.01746 0.00946 -0.0859 0.3839 1.0000
7.250 1.3210 0.01789 0.00984 -0.0853 0.3751 1.0000
7.500 1.3430 0.01832 0.01031 -0.0847 0.3660 1.0000
7.750 1.3647 0.01884 0.01073 -0.0840 0.3578 1.0000
8.000 1.3853 0.01931 0.01127 -0.0832 0.3486 1.0000
8.250 1.4053 0.01987 0.01179 -0.0823 0.3397 1.0000
8.500 1.4235 0.02041 0.01233 -0.0811 0.3298 1.0000
8.750 1.4403 0.02099 0.01294 -0.0798 0.3195 1.0000
9.000 1.4559 0.02165 0.01353 -0.0783 0.3098 1.0000
9.250 1.4696 0.02227 0.01422 -0.0766 0.2999 1.0000
9.500 1.4818 0.02297 0.01494 -0.0746 0.2914 1.0000
9.750 1.4911 0.02372 0.01569 -0.0723 0.2833 1.0000
10.000 1.5009 0.02455 0.01658 -0.0703 0.2754 1.0000
10.250 1.5097 0.02550 0.01754 -0.0683 0.2677 1.0000
10.500 1.5191 0.02651 0.01862 -0.0667 0.2603 1.0000
10.750 1.5276 0.02765 0.01979 -0.0652 0.2533 1.0000
11.000 1.5364 0.02888 0.02107 -0.0640 0.2467 1.0000
11.250 1.5444 0.03021 0.02247 -0.0629 0.2398 1.0000
11.500 1.5518 0.03168 0.02396 -0.0618 0.2337 1.0000
11.750 1.5602 0.03314 0.02553 -0.0610 0.2273 1.0000
12.250 1.5718 0.03659 0.02909 -0.0593 0.2143 1.0000
12.500 1.5744 0.03863 0.03113 -0.0584 0.2080 1.0000
12.750 1.5794 0.04055 0.03318 -0.0578 0.2011 1.0000
13.000 1.5801 0.04286 0.03550 -0.0570 0.1945 1.0000
13.250 1.5817 0.04517 0.03790 -0.0564 0.1869 1.0000
13.500 1.5804 0.04777 0.04053 -0.0558 0.1806 1.0000
13.750 1.5816 0.05021 0.04306 -0.0552 0.1742 1.0000
14.000 1.5787 0.05315 0.04604 -0.0548 0.1673 1.0000
14.250 1.5770 0.05611 0.04908 -0.0545 0.1592 1.0000
14.500 1.5707 0.05968 0.05268 -0.0543 0.1518 1.0000
14.750 1.5665 0.06317 0.05625 -0.0544 0.1404 1.0000
15.000 1.5594 0.06712 0.06023 -0.0546 0.1264 1.0000
15.250 1.5379 0.07299 0.06597 -0.0551 0.0927 1.0000
15.500 1.5092 0.07994 0.07277 -0.0559 0.0705 1.0000
15.750 1.4819 0.08688 0.07968 -0.0568 0.0538 1.0000
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Polar data table (+)
Polar graphs
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