GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 200,000 Max Cl/Cd: 77.69 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe321-il-200000.txt Download as CSV file: xf-goe321-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2609 0.09020 0.08702 -0.0338 0.9012 0.0480
-7.750 -0.2641 0.08689 0.08356 -0.0459 0.8696 0.0488
-7.500 -0.2567 0.08245 0.07902 -0.0493 0.8530 0.0491
-7.250 -0.2484 0.07934 0.07587 -0.0453 0.8399 0.0495
-7.000 -0.2382 0.07662 0.07308 -0.0438 0.8274 0.0501
-6.750 -0.2260 0.07384 0.07023 -0.0444 0.8152 0.0510
-6.500 -0.2124 0.07092 0.06723 -0.0464 0.8043 0.0524
-6.250 -0.1964 0.06768 0.06385 -0.0499 0.7939 0.0545
-6.000 -0.1636 0.06287 0.05854 -0.0635 0.7837 0.0576
-5.750 -0.1520 0.05902 0.05471 -0.0624 0.7751 0.0582
-5.500 -0.1364 0.05633 0.05202 -0.0620 0.7650 0.0589
-5.250 -0.1185 0.05391 0.04952 -0.0624 0.7568 0.0601
-5.000 -0.0972 0.05137 0.04688 -0.0637 0.7477 0.0620
-4.750 -0.0594 0.04924 0.04398 -0.0689 0.7407 0.0679
-4.500 -0.0430 0.04506 0.03996 -0.0691 0.7324 0.0689
-4.250 -0.0232 0.04287 0.03772 -0.0691 0.7259 0.0703
-4.000 0.0003 0.04086 0.03565 -0.0697 0.7178 0.0725
-3.500 0.0562 0.03637 0.03051 -0.0718 0.7049 0.0814
-3.250 0.0797 0.03443 0.02857 -0.0721 0.6984 0.0834
-3.000 0.1055 0.03294 0.02693 -0.0724 0.6934 0.0874
-2.750 0.1352 0.03126 0.02488 -0.0731 0.6876 0.0954
-2.500 0.1602 0.02968 0.02332 -0.0733 0.6818 0.0992
-2.250 0.1889 0.02853 0.02181 -0.0735 0.6773 0.1103
-2.000 0.2151 0.02708 0.02038 -0.0738 0.6720 0.1149
-1.750 0.2433 0.02593 0.01904 -0.0742 0.6666 0.1274
-1.500 0.2706 0.02496 0.01789 -0.0742 0.6616 0.1427
-1.250 0.2974 0.02390 0.01676 -0.0744 0.6556 0.1597
-0.750 0.3669 0.02017 0.01183 -0.0724 0.6442 0.0778
-0.500 0.3958 0.01896 0.01050 -0.0723 0.6378 0.0743
-0.250 0.4247 0.01807 0.00944 -0.0720 0.6316 0.0724
0.000 0.4531 0.01740 0.00860 -0.0716 0.6267 0.0723
0.250 0.4815 0.01688 0.00809 -0.0715 0.6199 0.0734
0.500 0.5097 0.01651 0.00767 -0.0713 0.6143 0.0769
0.750 0.5380 0.01621 0.00727 -0.0710 0.6097 0.0793
1.000 0.5654 0.01560 0.00680 -0.0709 0.6029 0.0827
1.250 0.5933 0.01524 0.00643 -0.0706 0.5968 0.0882
1.500 0.6210 0.01493 0.00616 -0.0705 0.5903 0.0985
1.750 0.6490 0.01463 0.00589 -0.0704 0.5835 0.1196
2.000 0.6782 0.01239 0.00564 -0.0702 0.5777 1.0000
2.250 0.7056 0.01248 0.00564 -0.0700 0.5696 1.0000
2.500 0.7333 0.01256 0.00556 -0.0698 0.5633 1.0000
2.750 0.7608 0.01270 0.00566 -0.0697 0.5562 1.0000
3.000 0.7884 0.01280 0.00567 -0.0695 0.5492 1.0000
3.250 0.8158 0.01295 0.00575 -0.0694 0.5422 1.0000
3.500 0.8431 0.01306 0.00582 -0.0692 0.5342 1.0000
3.750 0.8705 0.01321 0.00589 -0.0691 0.5267 1.0000
4.000 0.8975 0.01331 0.00598 -0.0689 0.5174 1.0000
4.250 0.9245 0.01344 0.00608 -0.0687 0.5084 1.0000
4.500 0.9514 0.01354 0.00613 -0.0684 0.4983 1.0000
4.750 0.9779 0.01365 0.00625 -0.0682 0.4869 1.0000
5.000 1.0044 0.01375 0.00634 -0.0680 0.4753 1.0000
5.250 1.0307 0.01385 0.00641 -0.0677 0.4625 1.0000
5.500 1.0567 0.01395 0.00651 -0.0674 0.4469 1.0000
5.750 1.0823 0.01406 0.00665 -0.0670 0.4272 1.0000
6.000 1.1071 0.01425 0.00677 -0.0666 0.4033 1.0000
6.250 1.1303 0.01460 0.00698 -0.0659 0.3749 1.0000
6.500 1.1518 0.01518 0.00735 -0.0651 0.3471 1.0000
6.750 1.1719 0.01593 0.00790 -0.0642 0.3235 1.0000
7.000 1.1925 0.01667 0.00852 -0.0633 0.3038 1.0000
7.250 1.2131 0.01741 0.00915 -0.0625 0.2888 1.0000
7.750 1.2557 0.01874 0.01039 -0.0610 0.2682 1.0000
8.000 1.2766 0.01948 0.01102 -0.0602 0.2614 1.0000
8.250 1.2990 0.02002 0.01162 -0.0596 0.2551 1.0000
8.500 1.3206 0.02064 0.01224 -0.0589 0.2500 1.0000
8.750 1.3425 0.02138 0.01291 -0.0583 0.2460 1.0000
9.000 1.3648 0.02195 0.01358 -0.0578 0.2424 1.0000
9.250 1.3869 0.02256 0.01427 -0.0572 0.2392 1.0000
9.500 1.4091 0.02319 0.01494 -0.0566 0.2363 1.0000
9.750 1.4317 0.02389 0.01563 -0.0561 0.2337 1.0000
10.000 1.4551 0.02470 0.01642 -0.0559 0.2308 1.0000
10.250 1.4743 0.02528 0.01719 -0.0549 0.2275 1.0000
10.500 1.4932 0.02589 0.01790 -0.0540 0.2236 1.0000
10.750 1.5120 0.02652 0.01855 -0.0531 0.2197 1.0000
11.000 1.5328 0.02735 0.01935 -0.0526 0.2157 1.0000
11.250 1.5469 0.02800 0.02021 -0.0511 0.2122 1.0000
11.500 1.5602 0.02866 0.02098 -0.0495 0.2081 1.0000
11.750 1.5733 0.02936 0.02167 -0.0479 0.2038 1.0000
12.000 1.5847 0.03024 0.02263 -0.0462 0.1997 1.0000
12.250 1.5901 0.03114 0.02372 -0.0440 0.1955 1.0000
12.500 1.5972 0.03209 0.02473 -0.0423 0.1909 1.0000
12.750 1.6066 0.03322 0.02585 -0.0410 0.1858 1.0000
13.000 1.6080 0.03462 0.02748 -0.0395 0.1814 1.0000
13.250 1.6127 0.03604 0.02899 -0.0384 0.1767 1.0000
13.500 1.6216 0.03740 0.03034 -0.0375 0.1720 1.0000
13.750 1.6212 0.03942 0.03263 -0.0368 0.1677 1.0000
14.000 1.6218 0.04150 0.03484 -0.0364 0.1624 1.0000
14.250 1.6219 0.04375 0.03714 -0.0359 0.1566 1.0000
14.500 1.6177 0.04663 0.04027 -0.0361 0.1496 1.0000
14.750 1.6118 0.04982 0.04357 -0.0363 0.1414 1.0000
15.000 1.6045 0.05354 0.04750 -0.0372 0.1264 1.0000
15.250 1.5870 0.05868 0.05255 -0.0382 0.0928 1.0000
15.500 1.5602 0.06503 0.05873 -0.0392 0.0747 1.0000
15.750 1.5354 0.07140 0.06507 -0.0402 0.0627 1.0000
16.000 1.5125 0.07778 0.07148 -0.0415 0.0554 1.0000
16.250 1.4909 0.08423 0.07801 -0.0430 0.0508 1.0000
16.500 1.4701 0.09081 0.08470 -0.0448 0.0479 1.0000
16.750 1.4509 0.09734 0.09136 -0.0468 0.0457 1.0000
17.000 1.4306 0.10426 0.09841 -0.0491 0.0442 1.0000
17.250 1.4096 0.11152 0.10579 -0.0518 0.0431 1.0000
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Polar data table (+)
Polar graphs
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