GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 500,000 Max Cl/Cd: 90.32 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe321-il-500000-n5.txt Download as CSV file: xf-goe321-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3103 0.08827 0.08498 -0.0208 0.6898 0.0202
-8.000 -0.3065 0.08432 0.08102 -0.0237 0.6846 0.0207
-7.750 -0.3040 0.08039 0.07708 -0.0271 0.6796 0.0208
-7.500 -0.2966 0.07488 0.07154 -0.0340 0.6750 0.0211
-7.250 -0.2861 0.06839 0.06499 -0.0423 0.6700 0.0216
-7.000 -0.2693 0.06632 0.06287 -0.0439 0.6639 0.0218
-6.750 -0.2516 0.06390 0.06042 -0.0462 0.6582 0.0222
-6.500 -0.2328 0.06090 0.05735 -0.0492 0.6518 0.0228
-6.250 -0.2131 0.05704 0.05339 -0.0530 0.6460 0.0232
-6.000 -0.1921 0.05267 0.04891 -0.0568 0.6398 0.0233
-5.750 -0.1697 0.04839 0.04447 -0.0601 0.6331 0.0235
-4.750 -0.0732 0.02553 0.02013 -0.0686 0.6078 0.0254
-4.500 -0.0471 0.02426 0.01868 -0.0689 0.5999 0.0258
-4.250 -0.0204 0.02335 0.01764 -0.0691 0.5923 0.0261
-4.000 0.0064 0.02172 0.01578 -0.0692 0.5849 0.0264
-3.750 0.0332 0.01915 0.01282 -0.0693 0.5787 0.0268
-3.500 0.0607 0.01725 0.01058 -0.0693 0.5727 0.0273
-3.250 0.0885 0.01591 0.00895 -0.0693 0.5675 0.0277
-3.000 0.1167 0.01493 0.00775 -0.0693 0.5629 0.0281
-2.750 0.1450 0.01417 0.00681 -0.0693 0.5575 0.0285
-2.500 0.1733 0.01365 0.00611 -0.0692 0.5510 0.0290
-2.250 0.2019 0.01325 0.00558 -0.0692 0.5444 0.0295
-2.000 0.2303 0.01290 0.00512 -0.0692 0.5375 0.0297
-1.750 0.2584 0.01239 0.00452 -0.0692 0.5317 0.0302
-1.500 0.2868 0.01206 0.00418 -0.0693 0.5264 0.0306
-1.250 0.3153 0.01183 0.00392 -0.0693 0.5212 0.0311
-1.000 0.3437 0.01165 0.00369 -0.0694 0.5165 0.0316
-0.750 0.3723 0.01145 0.00348 -0.0694 0.5115 0.0322
-0.500 0.4009 0.01127 0.00328 -0.0695 0.5058 0.0328
-0.250 0.4294 0.01114 0.00311 -0.0695 0.5010 0.0335
0.000 0.4581 0.01102 0.00297 -0.0696 0.4971 0.0343
0.250 0.4869 0.01089 0.00284 -0.0697 0.4923 0.0353
0.500 0.5155 0.01078 0.00274 -0.0698 0.4866 0.0366
0.750 0.5440 0.01073 0.00267 -0.0699 0.4821 0.0379
1.000 0.5729 0.01065 0.00261 -0.0700 0.4779 0.0394
1.250 0.6017 0.01060 0.00256 -0.0702 0.4721 0.0410
1.500 0.6302 0.01058 0.00253 -0.0703 0.4652 0.0440
1.750 0.6590 0.01054 0.00251 -0.0704 0.4578 0.0487
2.000 0.6875 0.01054 0.00252 -0.0705 0.4498 0.0590
2.250 0.7161 0.01051 0.00255 -0.0707 0.4410 0.0765
2.500 0.7445 0.01051 0.00259 -0.0708 0.4305 0.1056
2.750 0.7692 0.00861 0.00276 -0.0705 0.4160 1.0000
3.000 0.7966 0.00882 0.00282 -0.0705 0.3914 1.0000
3.250 0.8231 0.00915 0.00295 -0.0704 0.3605 1.0000
3.500 0.8494 0.00951 0.00313 -0.0703 0.3356 1.0000
3.750 0.8760 0.00982 0.00333 -0.0702 0.3174 1.0000
4.000 0.9027 0.01012 0.00352 -0.0701 0.3026 1.0000
4.250 0.9294 0.01041 0.00373 -0.0701 0.2892 1.0000
4.500 0.9559 0.01071 0.00394 -0.0700 0.2755 1.0000
4.750 0.9822 0.01102 0.00416 -0.0699 0.2613 1.0000
5.250 1.0342 0.01169 0.00466 -0.0696 0.2311 1.0000
5.500 1.0598 0.01205 0.00493 -0.0695 0.2165 1.0000
5.750 1.0853 0.01240 0.00521 -0.0693 0.2047 1.0000
6.000 1.1109 0.01272 0.00549 -0.0691 0.1967 1.0000
6.250 1.1362 0.01306 0.00579 -0.0689 0.1901 1.0000
6.500 1.1616 0.01338 0.00609 -0.0687 0.1857 1.0000
6.750 1.1870 0.01367 0.00639 -0.0685 0.1824 1.0000
7.000 1.2121 0.01399 0.00670 -0.0683 0.1794 1.0000
7.250 1.2367 0.01432 0.00704 -0.0680 0.1767 1.0000
7.500 1.2609 0.01469 0.00740 -0.0676 0.1743 1.0000
7.750 1.2849 0.01505 0.00778 -0.0673 0.1722 1.0000
8.000 1.3093 0.01536 0.00813 -0.0669 0.1711 1.0000
8.250 1.3334 0.01568 0.00850 -0.0666 0.1700 1.0000
8.500 1.3569 0.01602 0.00888 -0.0661 0.1686 1.0000
8.750 1.3800 0.01639 0.00928 -0.0657 0.1666 1.0000
9.000 1.4021 0.01680 0.00972 -0.0651 0.1638 1.0000
9.250 1.4231 0.01728 0.01020 -0.0644 0.1608 1.0000
9.500 1.4428 0.01782 0.01075 -0.0635 0.1582 1.0000
9.750 1.4632 0.01827 0.01126 -0.0627 0.1566 1.0000
10.000 1.4845 0.01864 0.01171 -0.0620 0.1553 1.0000
10.250 1.5048 0.01904 0.01217 -0.0612 0.1535 1.0000
10.500 1.5229 0.01950 0.01269 -0.0601 0.1510 1.0000
10.750 1.5383 0.02005 0.01329 -0.0586 0.1486 1.0000
11.000 1.5519 0.02074 0.01401 -0.0570 0.1456 1.0000
11.250 1.5638 0.02161 0.01490 -0.0554 0.1423 1.0000
11.500 1.5826 0.02210 0.01548 -0.0547 0.1390 1.0000
11.750 1.5980 0.02283 0.01627 -0.0538 0.1344 1.0000
12.000 1.6093 0.02392 0.01735 -0.0527 0.1288 1.0000
12.250 1.6232 0.02488 0.01834 -0.0519 0.1188 1.0000
12.500 1.6211 0.02730 0.02053 -0.0506 0.0877 1.0000
12.750 1.6094 0.03082 0.02393 -0.0493 0.0656 1.0000
13.000 1.6011 0.03416 0.02722 -0.0483 0.0495 1.0000
13.250 1.5903 0.03781 0.03082 -0.0473 0.0350 1.0000
13.500 1.5819 0.04128 0.03429 -0.0466 0.0255 1.0000
13.750 1.5775 0.04441 0.03746 -0.0461 0.0212 1.0000
14.000 1.5751 0.04738 0.04050 -0.0458 0.0190 1.0000
14.250 1.5725 0.05045 0.04365 -0.0456 0.0176 1.0000
14.500 1.5695 0.05362 0.04690 -0.0454 0.0165 1.0000
14.750 1.5678 0.05672 0.05010 -0.0454 0.0158 1.0000
15.000 1.5650 0.06007 0.05355 -0.0456 0.0151 1.0000
15.250 1.5611 0.06365 0.05723 -0.0459 0.0146 1.0000
15.500 1.5557 0.06749 0.06116 -0.0464 0.0141 1.0000
15.750 1.5487 0.07164 0.06542 -0.0469 0.0137 1.0000
16.000 1.5421 0.07580 0.06969 -0.0476 0.0133 1.0000
16.250 1.5359 0.07996 0.07396 -0.0484 0.0131 1.0000
16.500 1.5284 0.08438 0.07849 -0.0493 0.0128 1.0000
16.750 1.5195 0.08909 0.08333 -0.0503 0.0125 1.0000
17.000 1.5094 0.09409 0.08845 -0.0516 0.0123 1.0000
17.250 1.4977 0.09939 0.09387 -0.0531 0.0121 1.0000
17.500 1.4851 0.10497 0.09957 -0.0547 0.0119 1.0000
17.750 1.4719 0.11078 0.10550 -0.0566 0.0117 1.0000
18.000 1.4576 0.11685 0.11170 -0.0587 0.0115 1.0000
18.250 1.4426 0.12314 0.11810 -0.0611 0.0114 1.0000
18.500 1.4277 0.12952 0.12461 -0.0636 0.0113 1.0000
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