GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 100,000 Max Cl/Cd: 55.73 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe321-il-100000-n5.txt Download as CSV file: xf-goe321-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2968 0.11175 0.10706 -0.0206 1.0000 0.0546
-9.250 -0.2976 0.10946 0.10484 -0.0249 1.0000 0.0561
-9.000 -0.3024 0.10737 0.10284 -0.0303 1.0000 0.0566
-8.750 -0.2888 0.10275 0.09826 -0.0318 0.9663 0.0571
-8.500 -0.2677 0.09846 0.09393 -0.0315 0.9350 0.0583
-8.250 -0.2556 0.09518 0.09061 -0.0329 0.9000 0.0594
-8.000 -0.2479 0.09224 0.08760 -0.0341 0.8714 0.0605
-7.750 -0.2426 0.08940 0.08470 -0.0353 0.8494 0.0618
-7.500 -0.2388 0.08661 0.08184 -0.0373 0.8319 0.0632
-7.250 -0.1758 0.07189 0.06711 -0.0515 0.7858 0.0670
-7.000 -0.1611 0.06865 0.06383 -0.0465 0.7774 0.0684
-6.750 -0.1516 0.06546 0.06062 -0.0467 0.7685 0.0699
-6.500 -0.1439 0.06208 0.05717 -0.0484 0.7616 0.0714
-6.250 -0.1349 0.05844 0.05349 -0.0512 0.7535 0.0732
-6.000 -0.1244 0.05464 0.04958 -0.0549 0.7468 0.0756
-5.750 -0.1072 0.05040 0.04490 -0.0642 0.7396 0.0783
-5.500 -0.0943 0.04595 0.04043 -0.0647 0.7329 0.0789
-5.250 -0.0811 0.04258 0.03706 -0.0639 0.7271 0.0800
-5.000 -0.0655 0.03985 0.03433 -0.0637 0.7193 0.0819
-4.750 -0.0475 0.03715 0.03151 -0.0645 0.7131 0.0855
-4.500 -0.0204 0.03386 0.02767 -0.0688 0.7064 0.0924
-4.000 0.0206 0.03990 0.03245 -0.0734 0.7097 0.0564
-3.750 0.0442 0.03770 0.03019 -0.0738 0.7026 0.0555
-3.500 0.0698 0.03556 0.02782 -0.0742 0.6969 0.0547
-3.250 0.0973 0.03354 0.02544 -0.0746 0.6911 0.0553
-3.000 0.1250 0.03169 0.02328 -0.0749 0.6848 0.0556
-2.750 0.1521 0.03002 0.02130 -0.0749 0.6796 0.0551
-2.500 0.1799 0.02848 0.01950 -0.0751 0.6735 0.0547
-2.250 0.2081 0.02710 0.01783 -0.0751 0.6677 0.0545
-2.000 0.2363 0.02588 0.01630 -0.0750 0.6633 0.0545
-1.750 0.2649 0.02485 0.01501 -0.0750 0.6580 0.0548
-1.500 0.2936 0.02406 0.01391 -0.0749 0.6525 0.0564
-1.250 0.3213 0.02321 0.01295 -0.0748 0.6479 0.0579
-1.000 0.3494 0.02254 0.01219 -0.0748 0.6432 0.0588
-0.750 0.3774 0.02194 0.01152 -0.0747 0.6377 0.0597
-0.500 0.4052 0.02136 0.01084 -0.0745 0.6326 0.0608
-0.250 0.4328 0.02084 0.01027 -0.0742 0.6261 0.0623
0.000 0.4601 0.02040 0.00976 -0.0739 0.6188 0.0648
0.250 0.4872 0.01995 0.00927 -0.0735 0.6128 0.0682
0.500 0.5139 0.01962 0.00902 -0.0733 0.6059 0.0715
0.750 0.5409 0.01930 0.00866 -0.0728 0.6006 0.0751
1.000 0.5680 0.01907 0.00837 -0.0725 0.5944 0.0797
1.250 0.5950 0.01887 0.00817 -0.0723 0.5871 0.0893
1.500 0.6226 0.01864 0.00786 -0.0719 0.5806 0.1034
1.750 0.6500 0.01833 0.00775 -0.0719 0.5721 0.1528
2.000 0.6805 0.01633 0.00755 -0.0719 0.5647 1.0000
2.250 0.7070 0.01648 0.00757 -0.0716 0.5557 1.0000
2.500 0.7339 0.01658 0.00747 -0.0711 0.5481 1.0000
2.750 0.7602 0.01674 0.00755 -0.0708 0.5385 1.0000
3.000 0.7868 0.01687 0.00755 -0.0705 0.5303 1.0000
3.250 0.8130 0.01705 0.00767 -0.0701 0.5208 1.0000
3.500 0.8395 0.01722 0.00775 -0.0698 0.5128 1.0000
3.750 0.8656 0.01742 0.00793 -0.0695 0.5034 1.0000
4.000 0.8916 0.01762 0.00807 -0.0692 0.4942 1.0000
4.250 0.9174 0.01780 0.00822 -0.0688 0.4841 1.0000
4.500 0.9429 0.01803 0.00847 -0.0685 0.4727 1.0000
4.750 0.9683 0.01823 0.00866 -0.0681 0.4614 1.0000
5.000 0.9935 0.01844 0.00884 -0.0677 0.4491 1.0000
5.250 1.0182 0.01868 0.00912 -0.0673 0.4346 1.0000
5.500 1.0426 0.01893 0.00937 -0.0668 0.4186 1.0000
5.750 1.0664 0.01922 0.00964 -0.0662 0.4001 1.0000
6.000 1.0895 0.01955 0.00990 -0.0656 0.3806 1.0000
6.250 1.1115 0.01996 0.01020 -0.0648 0.3616 1.0000
6.500 1.1324 0.02049 0.01059 -0.0639 0.3436 1.0000
6.750 1.1525 0.02110 0.01111 -0.0629 0.3271 1.0000
7.000 1.1721 0.02178 0.01170 -0.0620 0.3122 1.0000
7.250 1.1913 0.02247 0.01235 -0.0610 0.2989 1.0000
7.500 1.2101 0.02320 0.01305 -0.0599 0.2873 1.0000
7.750 1.2281 0.02396 0.01375 -0.0588 0.2775 1.0000
8.000 1.2470 0.02466 0.01449 -0.0579 0.2686 1.0000
8.250 1.2645 0.02544 0.01522 -0.0567 0.2618 1.0000
8.500 1.2832 0.02616 0.01602 -0.0557 0.2553 1.0000
8.750 1.3007 0.02693 0.01680 -0.0546 0.2498 1.0000
9.000 1.3182 0.02773 0.01757 -0.0535 0.2455 1.0000
9.250 1.3364 0.02849 0.01843 -0.0525 0.2411 1.0000
9.500 1.3539 0.02928 0.01930 -0.0515 0.2372 1.0000
9.750 1.3711 0.03009 0.02013 -0.0504 0.2340 1.0000
10.000 1.3891 0.03090 0.02091 -0.0493 0.2314 1.0000
10.250 1.4054 0.03176 0.02192 -0.0482 0.2284 1.0000
10.500 1.4214 0.03266 0.02295 -0.0471 0.2253 1.0000
10.750 1.4375 0.03357 0.02396 -0.0460 0.2225 1.0000
11.000 1.4546 0.03448 0.02494 -0.0451 0.2201 1.0000
11.250 1.4735 0.03538 0.02589 -0.0444 0.2181 1.0000
11.500 1.4936 0.03630 0.02689 -0.0438 0.2163 1.0000
11.750 1.5075 0.03745 0.02824 -0.0427 0.2143 1.0000
12.000 1.5189 0.03867 0.02966 -0.0415 0.2117 1.0000
12.250 1.5292 0.03991 0.03105 -0.0403 0.2085 1.0000
12.500 1.5395 0.04105 0.03227 -0.0392 0.2047 1.0000
12.750 1.5464 0.04245 0.03374 -0.0380 0.2005 1.0000
13.000 1.5446 0.04443 0.03597 -0.0367 0.1961 1.0000
13.250 1.5470 0.04616 0.03780 -0.0357 0.1913 1.0000
13.500 1.5534 0.04768 0.03932 -0.0349 0.1867 1.0000
13.750 1.5468 0.05045 0.04238 -0.0343 0.1825 1.0000
14.000 1.5439 0.05294 0.04504 -0.0338 0.1777 1.0000
14.250 1.5480 0.05471 0.04673 -0.0333 0.1723 1.0000
14.500 1.5357 0.05848 0.05083 -0.0334 0.1681 1.0000
14.750 1.5268 0.06196 0.05449 -0.0336 0.1630 1.0000
15.000 1.5240 0.06466 0.05720 -0.0336 0.1576 1.0000
15.250 1.5107 0.06912 0.06194 -0.0344 0.1535 1.0000
15.500 1.4985 0.07365 0.06671 -0.0354 0.1490 1.0000
15.750 1.4902 0.07774 0.07092 -0.0364 0.1445 1.0000
16.000 1.4783 0.08261 0.07599 -0.0378 0.1403 1.0000
16.250 1.4592 0.08891 0.08258 -0.0398 0.1361 1.0000
16.500 1.4411 0.09521 0.08907 -0.0421 0.1317 1.0000
16.750 1.4211 0.10202 0.09606 -0.0447 0.1277 1.0000
17.000 1.3863 0.11180 0.10611 -0.0487 0.1255 1.0000
17.250 1.3383 0.12462 0.11915 -0.0545 0.1247 1.0000
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Polar data table (+)
Polar graphs
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