GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 200,000 Max Cl/Cd: 73.74 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe322-il-200000-n5.txt Download as CSV file: xf-goe322-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2054 0.09680 0.09248 -0.0443 0.7311 0.0386
-8.500 -0.2000 0.09302 0.08868 -0.0463 0.7275 0.0388
-8.250 -0.1862 0.09017 0.08584 -0.0449 0.7230 0.0392
-8.000 -0.1752 0.08750 0.08316 -0.0451 0.7185 0.0398
-7.750 -0.1664 0.08476 0.08040 -0.0462 0.7145 0.0404
-7.500 -0.1593 0.08195 0.07755 -0.0480 0.7107 0.0412
-7.250 -0.1521 0.07890 0.07453 -0.0508 0.7063 0.0422
-7.000 -0.1396 0.07225 0.06776 -0.0670 0.7023 0.0455
-6.750 -0.1271 0.06821 0.06366 -0.0694 0.6987 0.0459
-6.500 -0.1137 0.06596 0.06138 -0.0685 0.6952 0.0464
-6.250 -0.0975 0.06330 0.05872 -0.0697 0.6906 0.0470
-6.000 -0.0797 0.06038 0.05575 -0.0719 0.6859 0.0479
-5.500 -0.0329 0.04572 0.04034 -0.0844 0.6794 0.0386
-5.250 -0.0121 0.04348 0.03804 -0.0852 0.6753 0.0382
-5.000 0.0105 0.04078 0.03521 -0.0863 0.6707 0.0376
-4.750 0.0345 0.03758 0.03178 -0.0875 0.6666 0.0370
-4.500 0.0596 0.03419 0.02807 -0.0886 0.6630 0.0366
-4.250 0.0856 0.03069 0.02421 -0.0894 0.6586 0.0363
-4.000 0.1123 0.02736 0.02044 -0.0900 0.6541 0.0371
-3.750 0.1393 0.02480 0.01745 -0.0902 0.6499 0.0371
-3.500 0.1667 0.02278 0.01500 -0.0903 0.6463 0.0370
-3.250 0.1948 0.02122 0.01311 -0.0904 0.6411 0.0372
-3.000 0.2230 0.02001 0.01162 -0.0905 0.6357 0.0374
-2.750 0.2512 0.01905 0.01037 -0.0904 0.6305 0.0378
-2.500 0.2795 0.01827 0.00941 -0.0904 0.6228 0.0381
-2.250 0.3077 0.01766 0.00861 -0.0903 0.6160 0.0387
-2.000 0.3357 0.01702 0.00795 -0.0903 0.6096 0.0398
-1.750 0.3639 0.01659 0.00748 -0.0904 0.6037 0.0407
-1.500 0.3920 0.01616 0.00696 -0.0903 0.5988 0.0414
-1.250 0.4203 0.01578 0.00656 -0.0904 0.5929 0.0420
-1.000 0.4484 0.01545 0.00619 -0.0904 0.5870 0.0428
-0.750 0.4765 0.01517 0.00584 -0.0903 0.5821 0.0438
-0.500 0.5048 0.01495 0.00560 -0.0904 0.5759 0.0449
-0.250 0.5329 0.01474 0.00537 -0.0904 0.5701 0.0462
0.000 0.5610 0.01460 0.00520 -0.0904 0.5647 0.0486
0.250 0.5893 0.01450 0.00512 -0.0905 0.5580 0.0528
0.500 0.6174 0.01440 0.00502 -0.0905 0.5522 0.0586
0.750 0.6456 0.01433 0.00494 -0.0906 0.5466 0.0710
1.000 0.6735 0.01422 0.00491 -0.0907 0.5400 0.0943
1.250 0.7013 0.01416 0.00489 -0.0907 0.5341 0.1366
1.500 0.7290 0.01406 0.00494 -0.0908 0.5268 0.1842
2.000 0.7856 0.01239 0.00504 -0.0910 0.5120 1.0000
2.250 0.8127 0.01253 0.00507 -0.0909 0.5038 1.0000
2.500 0.8398 0.01268 0.00513 -0.0908 0.4948 1.0000
2.750 0.8666 0.01285 0.00517 -0.0906 0.4857 1.0000
3.000 0.8936 0.01301 0.00528 -0.0906 0.4760 1.0000
3.250 0.9201 0.01320 0.00537 -0.0904 0.4666 1.0000
3.500 0.9464 0.01339 0.00548 -0.0903 0.4553 1.0000
3.750 0.9726 0.01360 0.00563 -0.0901 0.4431 1.0000
4.000 0.9984 0.01383 0.00577 -0.0899 0.4313 1.0000
4.250 1.0239 0.01408 0.00594 -0.0896 0.4204 1.0000
4.500 1.0495 0.01433 0.00615 -0.0894 0.4096 1.0000
4.750 1.0747 0.01461 0.00637 -0.0891 0.3993 1.0000
5.000 1.0992 0.01492 0.00661 -0.0888 0.3892 1.0000
5.250 1.1238 0.01524 0.00688 -0.0885 0.3791 1.0000
5.500 1.1479 0.01558 0.00717 -0.0881 0.3699 1.0000
5.750 1.1714 0.01595 0.00749 -0.0876 0.3609 1.0000
6.000 1.1950 0.01631 0.00784 -0.0871 0.3524 1.0000
6.250 1.2174 0.01673 0.00821 -0.0865 0.3441 1.0000
6.500 1.2403 0.01712 0.00859 -0.0860 0.3361 1.0000
6.750 1.2616 0.01758 0.00902 -0.0853 0.3282 1.0000
7.000 1.2836 0.01800 0.00944 -0.0846 0.3209 1.0000
7.250 1.3042 0.01848 0.00991 -0.0838 0.3136 1.0000
7.500 1.3247 0.01895 0.01040 -0.0830 0.3072 1.0000
7.750 1.3447 0.01943 0.01090 -0.0821 0.3004 1.0000
8.000 1.3625 0.02000 0.01145 -0.0809 0.2943 1.0000
8.250 1.3813 0.02050 0.01200 -0.0799 0.2865 1.0000
8.500 1.3952 0.02118 0.01267 -0.0782 0.2782 1.0000
8.750 1.4083 0.02180 0.01332 -0.0763 0.2687 1.0000
9.000 1.4193 0.02259 0.01411 -0.0744 0.2601 1.0000
9.250 1.4298 0.02348 0.01501 -0.0726 0.2507 1.0000
9.500 1.4408 0.02444 0.01600 -0.0711 0.2412 1.0000
9.750 1.4492 0.02564 0.01719 -0.0695 0.2319 1.0000
10.000 1.4589 0.02687 0.01844 -0.0683 0.2229 1.0000
10.250 1.4679 0.02822 0.01981 -0.0673 0.2152 1.0000
10.500 1.4756 0.02975 0.02135 -0.0662 0.2073 1.0000
11.000 1.4891 0.03312 0.02477 -0.0644 0.1927 1.0000
11.250 1.4955 0.03488 0.02657 -0.0636 0.1857 1.0000
11.500 1.4984 0.03699 0.02867 -0.0627 0.1784 1.0000
11.750 1.5035 0.03891 0.03064 -0.0619 0.1720 1.0000
12.000 1.5059 0.04112 0.03288 -0.0611 0.1653 1.0000
12.250 1.5082 0.04336 0.03517 -0.0603 0.1585 1.0000
12.500 1.5093 0.04576 0.03760 -0.0596 0.1510 1.0000
12.750 1.5112 0.04813 0.04002 -0.0590 0.1442 1.0000
13.000 1.5091 0.05094 0.04284 -0.0584 0.1335 1.0000
13.250 1.5030 0.05429 0.04615 -0.0579 0.1120 1.0000
13.500 1.4764 0.06016 0.05177 -0.0575 0.0758 1.0000
13.750 1.4508 0.06616 0.05766 -0.0573 0.0521 1.0000
14.000 1.4283 0.07210 0.06355 -0.0574 0.0272 1.0000
14.250 1.4158 0.07696 0.06845 -0.0578 0.0223 1.0000
14.500 1.4084 0.08127 0.07287 -0.0582 0.0205 1.0000
14.750 1.4017 0.08556 0.07729 -0.0588 0.0195 1.0000
15.000 1.3938 0.09013 0.08200 -0.0595 0.0187 1.0000
15.250 1.3848 0.09494 0.08694 -0.0604 0.0180 1.0000
15.500 1.3774 0.09960 0.09175 -0.0614 0.0175 1.0000
15.750 1.3692 0.10446 0.09677 -0.0626 0.0171 1.0000
16.000 1.3600 0.10957 0.10203 -0.0639 0.0168 1.0000
16.250 1.3501 0.11486 0.10748 -0.0654 0.0165 1.0000
16.500 1.3395 0.12038 0.11315 -0.0671 0.0163 1.0000
16.750 1.3283 0.12610 0.11902 -0.0691 0.0161 1.0000
17.000 1.3170 0.13196 0.12503 -0.0712 0.0159 1.0000
17.250 1.3053 0.13794 0.13116 -0.0736 0.0158 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il)