GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 200,000 Max Cl/Cd: 74.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe324-il-200000-n5.txt Download as CSV file: xf-goe324-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 324 (HANSA-BRANDENBURG) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2334 0.09258 0.08787 -0.0130 0.6286 0.0352
-7.500 -0.2253 0.08959 0.08488 -0.0150 0.6248 0.0356
-7.250 -0.2174 0.08656 0.08182 -0.0172 0.6215 0.0361
-7.000 -0.2110 0.08358 0.07884 -0.0198 0.6181 0.0366
-6.750 -0.1999 0.08008 0.07534 -0.0243 0.6140 0.0373
-6.500 -0.1847 0.07561 0.07081 -0.0327 0.6102 0.0382
-6.250 -0.1649 0.07036 0.06542 -0.0419 0.6066 0.0386
-6.000 -0.1519 0.06785 0.06290 -0.0410 0.6027 0.0389
-5.750 -0.1361 0.06530 0.06032 -0.0417 0.5986 0.0394
-5.500 -0.1176 0.06248 0.05748 -0.0437 0.5940 0.0400
-5.250 -0.0970 0.05943 0.05436 -0.0464 0.5898 0.0408
-5.000 -0.0746 0.05626 0.05107 -0.0493 0.5860 0.0418
-4.750 -0.0393 0.05144 0.04575 -0.0561 0.5829 0.0439
-4.500 -0.0177 0.04828 0.04252 -0.0574 0.5783 0.0442
-4.250 0.0025 0.04601 0.04026 -0.0578 0.5732 0.0446
-4.000 0.0248 0.04391 0.03808 -0.0584 0.5687 0.0452
-3.750 0.0491 0.04178 0.03580 -0.0593 0.5648 0.0463
-3.500 0.0829 0.03885 0.03234 -0.0612 0.5603 0.0502
-3.250 0.1051 0.03679 0.03035 -0.0616 0.5554 0.0509
-3.000 0.1297 0.03514 0.02862 -0.0620 0.5510 0.0520
-2.750 0.1624 0.03400 0.02686 -0.0623 0.5474 0.0567
-2.500 0.1877 0.03146 0.02427 -0.0629 0.5423 0.0574
-2.250 0.2184 0.02699 0.01926 -0.0625 0.5379 0.0388
-2.000 0.2454 0.02570 0.01785 -0.0626 0.5332 0.0378
-1.750 0.2733 0.02434 0.01627 -0.0626 0.5292 0.0373
-1.500 0.3021 0.02307 0.01479 -0.0626 0.5242 0.0374
-1.250 0.3311 0.02197 0.01340 -0.0625 0.5195 0.0379
-1.000 0.3597 0.02099 0.01220 -0.0624 0.5155 0.0377
-0.750 0.3883 0.02013 0.01114 -0.0623 0.5115 0.0375
-0.500 0.4171 0.01935 0.01023 -0.0623 0.5064 0.0373
-0.250 0.4458 0.01868 0.00940 -0.0622 0.5017 0.0373
0.000 0.4744 0.01810 0.00866 -0.0620 0.4978 0.0374
0.250 0.5030 0.01762 0.00808 -0.0620 0.4938 0.0377
0.500 0.5315 0.01721 0.00761 -0.0619 0.4894 0.0380
0.750 0.5598 0.01684 0.00719 -0.0618 0.4851 0.0391
1.000 0.5876 0.01655 0.00689 -0.0618 0.4812 0.0404
1.250 0.6157 0.01629 0.00663 -0.0617 0.4774 0.0412
1.500 0.6438 0.01606 0.00643 -0.0617 0.4731 0.0418
1.750 0.6718 0.01587 0.00623 -0.0616 0.4690 0.0425
2.000 0.6997 0.01573 0.00605 -0.0616 0.4652 0.0434
2.250 0.7275 0.01561 0.00593 -0.0616 0.4610 0.0444
2.500 0.7554 0.01552 0.00590 -0.0616 0.4551 0.0467
2.750 0.7833 0.01550 0.00582 -0.0616 0.4493 0.0496
3.000 0.8110 0.01549 0.00576 -0.0615 0.4443 0.0521
3.250 0.8390 0.01552 0.00581 -0.0616 0.4393 0.0559
3.500 0.8668 0.01555 0.00586 -0.0616 0.4350 0.0645
3.750 0.8952 0.01374 0.00602 -0.0617 0.4311 1.0000
4.000 0.9226 0.01395 0.00613 -0.0617 0.4274 1.0000
4.250 0.9499 0.01414 0.00630 -0.0616 0.4229 1.0000
4.500 0.9771 0.01435 0.00646 -0.0616 0.4184 1.0000
4.750 1.0040 0.01456 0.00659 -0.0615 0.4143 1.0000
5.000 1.0310 0.01479 0.00678 -0.0614 0.4102 1.0000
5.250 1.0579 0.01501 0.00703 -0.0614 0.4055 1.0000
5.500 1.0845 0.01524 0.00723 -0.0613 0.4006 1.0000
5.750 1.1108 0.01548 0.00738 -0.0612 0.3959 1.0000
6.000 1.1372 0.01572 0.00769 -0.0612 0.3899 1.0000
6.250 1.1633 0.01596 0.00792 -0.0611 0.3839 1.0000
6.500 1.1890 0.01623 0.00814 -0.0609 0.3787 1.0000
6.750 1.2148 0.01649 0.00847 -0.0609 0.3725 1.0000
7.000 1.2401 0.01677 0.00875 -0.0607 0.3665 1.0000
7.250 1.2652 0.01708 0.00906 -0.0605 0.3608 1.0000
7.500 1.2901 0.01739 0.00942 -0.0604 0.3543 1.0000
7.750 1.3144 0.01772 0.00974 -0.0601 0.3484 1.0000
8.000 1.3386 0.01807 0.01015 -0.0599 0.3417 1.0000
8.250 1.3619 0.01845 0.01054 -0.0596 0.3345 1.0000
8.500 1.3849 0.01885 0.01097 -0.0593 0.3273 1.0000
8.750 1.4070 0.01929 0.01145 -0.0589 0.3196 1.0000
9.000 1.4285 0.01977 0.01195 -0.0584 0.3123 1.0000
9.250 1.4488 0.02029 0.01250 -0.0579 0.3046 1.0000
9.500 1.4684 0.02087 0.01309 -0.0572 0.2975 1.0000
9.750 1.4866 0.02150 0.01376 -0.0565 0.2903 1.0000
10.000 1.5032 0.02221 0.01449 -0.0557 0.2839 1.0000
10.250 1.5176 0.02300 0.01532 -0.0547 0.2765 1.0000
10.500 1.5270 0.02399 0.01632 -0.0532 0.2702 1.0000
10.750 1.5377 0.02508 0.01747 -0.0522 0.2638 1.0000
11.000 1.5462 0.02644 0.01885 -0.0514 0.2586 1.0000
11.250 1.5562 0.02780 0.02028 -0.0508 0.2539 1.0000
11.500 1.5658 0.02927 0.02182 -0.0504 0.2491 1.0000
11.750 1.5732 0.03093 0.02352 -0.0499 0.2447 1.0000
12.000 1.5805 0.03262 0.02525 -0.0494 0.2408 1.0000
12.250 1.5884 0.03431 0.02703 -0.0491 0.2364 1.0000
12.500 1.5939 0.03621 0.02899 -0.0487 0.2319 1.0000
12.750 1.5974 0.03826 0.03106 -0.0482 0.2276 1.0000
13.000 1.6028 0.04021 0.03311 -0.0478 0.2236 1.0000
13.250 1.6068 0.04231 0.03530 -0.0475 0.2193 1.0000
13.500 1.6085 0.04460 0.03763 -0.0471 0.2150 1.0000
13.750 1.6101 0.04690 0.03998 -0.0467 0.2110 1.0000
14.000 1.6111 0.04938 0.04259 -0.0465 0.2063 1.0000
14.250 1.6092 0.05214 0.04540 -0.0463 0.2012 1.0000
14.500 1.6067 0.05501 0.04830 -0.0462 0.1962 1.0000
14.750 1.6046 0.05807 0.05150 -0.0463 0.1903 1.0000
15.000 1.6000 0.06144 0.05489 -0.0465 0.1846 1.0000
15.250 1.5969 0.06476 0.05833 -0.0469 0.1788 1.0000
15.500 1.5919 0.06836 0.06200 -0.0473 0.1727 1.0000
15.750 1.5870 0.07199 0.06569 -0.0477 0.1672 1.0000
16.000 1.5821 0.07571 0.06952 -0.0483 0.1607 1.0000
16.250 1.5739 0.07990 0.07375 -0.0490 0.1545 1.0000
16.500 1.5661 0.08412 0.07806 -0.0498 0.1471 1.0000
16.750 1.5565 0.08864 0.08263 -0.0508 0.1399 1.0000
17.000 1.5449 0.09349 0.08752 -0.0518 0.1324 1.0000
17.250 1.5348 0.09816 0.09224 -0.0529 0.1251 1.0000
17.500 1.5228 0.10316 0.09727 -0.0542 0.1190 1.0000
17.750 1.5124 0.10801 0.10217 -0.0555 0.1133 1.0000
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