GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 50,000 Max Cl/Cd: 34.14 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe321-il-50000-n5.txt Download as CSV file: xf-goe321-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2884 0.11383 0.10728 -0.0230 1.0000 0.1018
-9.000 -0.2913 0.11228 0.10583 -0.0263 1.0000 0.1052
-8.750 -0.3022 0.11164 0.10535 -0.0307 1.0000 0.1063
-8.500 -0.2855 0.10622 0.09998 -0.0297 1.0000 0.1083
-8.250 -0.2709 0.10240 0.09621 -0.0289 1.0000 0.1117
-8.000 -0.2677 0.09994 0.09388 -0.0295 1.0000 0.1145
-7.750 -0.2761 0.09861 0.09272 -0.0290 0.9999 0.1167
-7.500 -0.2663 0.09615 0.09022 -0.0435 0.9620 0.1219
-7.250 -0.2449 0.09100 0.08508 -0.0463 0.9471 0.1239
-7.000 -0.2217 0.08682 0.08088 -0.0464 0.9331 0.1278
-6.750 -0.2041 0.08358 0.07756 -0.0518 0.9150 0.1353
-6.250 -0.1720 0.07685 0.07074 -0.0572 0.8846 0.1478
-6.000 -0.1584 0.07393 0.06768 -0.0632 0.8698 0.1575
-5.750 -0.1414 0.07080 0.06454 -0.0623 0.8587 0.1632
-5.250 -0.1085 0.06579 0.05923 -0.0680 0.8354 0.1878
-5.000 -0.0928 0.06259 0.05602 -0.0676 0.8258 0.1951
-4.750 -0.0759 0.06011 0.05345 -0.0687 0.8161 0.2112
-4.250 -0.0013 0.05118 0.04333 -0.0804 0.7988 0.1035
-4.000 0.0280 0.04812 0.03970 -0.0823 0.7906 0.0908
-3.750 0.0506 0.04570 0.03717 -0.0826 0.7827 0.0883
-3.500 0.0758 0.04347 0.03466 -0.0832 0.7751 0.0854
-3.250 0.1024 0.04137 0.03219 -0.0838 0.7672 0.0827
-3.000 0.1310 0.03940 0.02973 -0.0841 0.7614 0.0807
-2.750 0.1562 0.03807 0.02818 -0.0844 0.7533 0.0816
-2.500 0.1832 0.03675 0.02659 -0.0845 0.7472 0.0829
-2.250 0.2105 0.03556 0.02510 -0.0847 0.7405 0.0834
-2.000 0.2381 0.03443 0.02367 -0.0847 0.7336 0.0830
-1.750 0.2670 0.03334 0.02226 -0.0846 0.7286 0.0830
-1.500 0.2937 0.03261 0.02132 -0.0846 0.7215 0.0834
-1.250 0.3214 0.03191 0.02039 -0.0845 0.7155 0.0848
-1.000 0.3502 0.03127 0.01950 -0.0842 0.7108 0.0880
-0.750 0.3759 0.03102 0.01907 -0.0841 0.7031 0.0906
-0.500 0.4036 0.03052 0.01839 -0.0836 0.6976 0.0924
-0.250 0.4312 0.03006 0.01786 -0.0833 0.6919 0.0948
0.000 0.4567 0.02987 0.01762 -0.0829 0.6844 0.0983
0.250 0.4845 0.02951 0.01710 -0.0822 0.6789 0.1050
0.500 0.5074 0.02944 0.01707 -0.0817 0.6698 0.1112
0.750 0.5342 0.02910 0.01662 -0.0809 0.6635 0.1194
1.000 0.5573 0.02912 0.01669 -0.0804 0.6547 0.1327
1.250 0.5840 0.02881 0.01643 -0.0799 0.6483 0.1568
1.500 0.6115 0.02668 0.01653 -0.0798 0.6408 1.0000
1.750 0.6370 0.02701 0.01649 -0.0790 0.6336 1.0000
2.000 0.6615 0.02741 0.01665 -0.0784 0.6264 1.0000
2.250 0.6854 0.02782 0.01690 -0.0777 0.6184 1.0000
2.500 0.7105 0.02812 0.01704 -0.0770 0.6113 1.0000
3.000 0.7582 0.02879 0.01751 -0.0755 0.5938 1.0000
3.250 0.7841 0.02878 0.01740 -0.0746 0.5846 1.0000
3.500 0.8066 0.02901 0.01756 -0.0736 0.5727 1.0000
3.750 0.8325 0.02884 0.01727 -0.0725 0.5617 1.0000
4.000 0.8595 0.02854 0.01685 -0.0714 0.5506 1.0000
4.250 0.8814 0.02875 0.01703 -0.0703 0.5372 1.0000
4.500 0.9047 0.02891 0.01716 -0.0693 0.5254 1.0000
4.750 0.9322 0.02876 0.01692 -0.0685 0.5162 1.0000
5.000 0.9521 0.02928 0.01749 -0.0675 0.5031 1.0000
5.250 0.9735 0.02966 0.01788 -0.0665 0.4907 1.0000
5.500 0.9975 0.02981 0.01801 -0.0656 0.4794 1.0000
5.750 1.0190 0.03013 0.01836 -0.0645 0.4667 1.0000
6.000 1.0375 0.03069 0.01897 -0.0634 0.4522 1.0000
6.250 1.0561 0.03120 0.01955 -0.0622 0.4374 1.0000
6.500 1.0745 0.03170 0.02008 -0.0610 0.4225 1.0000
6.750 1.0928 0.03218 0.02058 -0.0597 0.4075 1.0000
7.000 1.1113 0.03265 0.02106 -0.0585 0.3928 1.0000
7.250 1.1299 0.03315 0.02151 -0.0572 0.3789 1.0000
7.500 1.1484 0.03369 0.02200 -0.0559 0.3661 1.0000
7.750 1.1680 0.03421 0.02243 -0.0547 0.3548 1.0000
8.000 1.1855 0.03500 0.02319 -0.0535 0.3438 1.0000
8.250 1.2015 0.03599 0.02419 -0.0523 0.3336 1.0000
8.750 1.2353 0.03798 0.02616 -0.0501 0.3163 1.0000
9.000 1.2582 0.03863 0.02674 -0.0494 0.3094 1.0000
9.250 1.2675 0.04025 0.02852 -0.0480 0.3019 1.0000
9.500 1.2863 0.04122 0.02951 -0.0471 0.2957 1.0000
9.750 1.3029 0.04243 0.03078 -0.0461 0.2904 1.0000
10.000 1.3107 0.04420 0.03276 -0.0447 0.2854 1.0000
10.250 1.3268 0.04553 0.03418 -0.0439 0.2811 1.0000
10.500 1.3540 0.04629 0.03496 -0.0437 0.2775 1.0000
10.750 1.3542 0.04871 0.03762 -0.0422 0.2739 1.0000
11.000 1.3521 0.05142 0.04057 -0.0408 0.2703 1.0000
11.250 1.3565 0.05374 0.04308 -0.0398 0.2669 1.0000
11.500 1.3732 0.05512 0.04457 -0.0392 0.2637 1.0000
11.750 1.3894 0.05662 0.04617 -0.0386 0.2607 1.0000
12.000 1.3420 0.06385 0.05374 -0.0380 0.2574 1.0000
12.250 1.2534 0.07811 0.06825 -0.0410 0.2525 1.0000
12.500 1.2176 0.08721 0.07748 -0.0435 0.2487 1.0000
12.750 1.2275 0.08951 0.07991 -0.0432 0.2467 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)