GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 200,000 Max Cl/Cd: 80.78 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe238-il-200000-n5.txt Download as CSV file: xf-goe238-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 238 (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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2161 0.09485 0.09025 -0.0444 0.7049 0.0341
-8.500 -0.2161 0.09229 0.08767 -0.0466 0.6975 0.0342
-8.250 -0.2043 0.08868 0.08405 -0.0462 0.6902 0.0345
-8.000 -0.1921 0.08581 0.08113 -0.0458 0.6826 0.0349
-7.750 -0.1839 0.08332 0.07862 -0.0460 0.6758 0.0355
-7.500 -0.1779 0.08095 0.07625 -0.0466 0.6688 0.0363
-7.250 -0.1748 0.07864 0.07391 -0.0473 0.6628 0.0367
-7.000 -0.1702 0.07618 0.07144 -0.0487 0.6569 0.0374
-6.750 -0.1625 0.07344 0.06868 -0.0509 0.6509 0.0383
-6.500 -0.1532 0.07048 0.06564 -0.0552 0.6456 0.0396
-6.250 -0.1388 0.06712 0.06218 -0.0610 0.6401 0.0400
-6.000 -0.1209 0.06361 0.05850 -0.0655 0.6344 0.0402
-5.750 -0.1099 0.06048 0.05537 -0.0646 0.6290 0.0406
-5.500 -0.0959 0.05814 0.05304 -0.0641 0.6232 0.0412
-5.250 -0.0793 0.05576 0.05060 -0.0648 0.6174 0.0419
-5.000 -0.0607 0.05323 0.04797 -0.0661 0.6125 0.0426
-4.750 -0.0404 0.05065 0.04529 -0.0676 0.6075 0.0437
-4.500 -0.0179 0.04798 0.04249 -0.0693 0.6022 0.0451
-4.250 0.0156 0.04473 0.03877 -0.0729 0.5977 0.0471
-4.000 0.0392 0.04184 0.03559 -0.0737 0.5935 0.0473
-3.750 0.0562 0.03931 0.03315 -0.0736 0.5879 0.0480
-3.500 0.0765 0.03767 0.03148 -0.0736 0.5827 0.0489
-3.250 0.0995 0.03588 0.02955 -0.0737 0.5782 0.0501
-3.000 0.1308 0.03077 0.02373 -0.0740 0.5742 0.0401
-2.750 0.1538 0.02914 0.02205 -0.0740 0.5692 0.0395
-2.500 0.1783 0.02738 0.02010 -0.0738 0.5649 0.0389
-2.250 0.2036 0.02558 0.01802 -0.0735 0.5612 0.0384
-2.000 0.2299 0.02391 0.01607 -0.0731 0.5569 0.0388
-1.750 0.2567 0.02246 0.01427 -0.0726 0.5525 0.0395
-1.500 0.2829 0.02124 0.01280 -0.0722 0.5484 0.0393
-1.250 0.3094 0.02017 0.01145 -0.0717 0.5449 0.0392
-1.000 0.3363 0.01922 0.01030 -0.0714 0.5406 0.0393
-0.750 0.3634 0.01841 0.00930 -0.0710 0.5362 0.0395
-0.500 0.3905 0.01774 0.00842 -0.0706 0.5323 0.0399
-0.250 0.4175 0.01717 0.00766 -0.0702 0.5290 0.0404
0.000 0.4443 0.01671 0.00720 -0.0700 0.5256 0.0417
0.250 0.4713 0.01640 0.00689 -0.0697 0.5218 0.0432
0.500 0.4983 0.01601 0.00645 -0.0694 0.5181 0.0440
0.750 0.5252 0.01565 0.00602 -0.0690 0.5145 0.0448
1.000 0.5519 0.01535 0.00565 -0.0686 0.5110 0.0457
1.250 0.5785 0.01509 0.00541 -0.0682 0.5064 0.0467
1.500 0.6047 0.01482 0.00517 -0.0678 0.5021 0.0481
1.750 0.6309 0.01466 0.00506 -0.0675 0.4984 0.0507
2.000 0.6572 0.01457 0.00493 -0.0671 0.4951 0.0537
2.250 0.6835 0.01445 0.00487 -0.0667 0.4911 0.0557
2.500 0.7096 0.01433 0.00480 -0.0663 0.4874 0.0589
2.750 0.7360 0.01431 0.00478 -0.0660 0.4841 0.0638
3.000 0.7622 0.01427 0.00473 -0.0656 0.4812 0.0724
3.500 0.8400 0.01255 0.00498 -0.0706 0.4734 1.0000
3.750 0.8657 0.01269 0.00508 -0.0701 0.4694 1.0000
4.000 0.8914 0.01285 0.00518 -0.0697 0.4661 1.0000
4.250 0.9172 0.01303 0.00529 -0.0692 0.4632 1.0000
4.500 0.9428 0.01320 0.00549 -0.0688 0.4597 1.0000
4.750 0.9682 0.01336 0.00568 -0.0683 0.4552 1.0000
5.000 0.9935 0.01350 0.00581 -0.0678 0.4501 1.0000
5.250 1.0188 0.01366 0.00593 -0.0673 0.4451 1.0000
5.500 1.0436 0.01380 0.00614 -0.0668 0.4378 1.0000
5.750 1.0684 0.01394 0.00625 -0.0662 0.4313 1.0000
6.000 1.0930 0.01409 0.00646 -0.0656 0.4229 1.0000
6.250 1.1173 0.01425 0.00660 -0.0650 0.4149 1.0000
6.500 1.1420 0.01444 0.00688 -0.0645 0.4078 1.0000
6.750 1.1662 0.01464 0.00710 -0.0639 0.4007 1.0000
7.000 1.1903 0.01485 0.00737 -0.0633 0.3922 1.0000
7.250 1.2136 0.01507 0.00762 -0.0626 0.3821 1.0000
7.500 1.2367 0.01531 0.00791 -0.0619 0.3686 1.0000
7.750 1.2587 0.01559 0.00820 -0.0610 0.3504 1.0000
8.000 1.2796 0.01595 0.00854 -0.0600 0.3267 1.0000
8.250 1.2963 0.01654 0.00899 -0.0585 0.2924 1.0000
8.500 1.3093 0.01741 0.00967 -0.0566 0.2631 1.0000
8.750 1.3226 0.01827 0.01045 -0.0548 0.2443 1.0000
9.000 1.3347 0.01917 0.01129 -0.0528 0.2287 1.0000
9.500 1.3589 0.02083 0.01297 -0.0490 0.2053 1.0000
9.750 1.3679 0.02169 0.01385 -0.0467 0.1942 1.0000
10.000 1.3724 0.02268 0.01485 -0.0438 0.1791 1.0000
10.250 1.3736 0.02396 0.01609 -0.0410 0.1565 1.0000
10.500 1.3566 0.02676 0.01862 -0.0381 0.1124 1.0000
10.750 1.3440 0.02985 0.02154 -0.0364 0.0899 1.0000
11.000 1.3393 0.03251 0.02417 -0.0353 0.0807 1.0000
11.250 1.3386 0.03491 0.02662 -0.0345 0.0756 1.0000
11.500 1.3379 0.03737 0.02913 -0.0338 0.0718 1.0000
11.750 1.3349 0.04013 0.03194 -0.0332 0.0685 1.0000
12.000 1.3365 0.04249 0.03438 -0.0328 0.0658 1.0000
12.250 1.3366 0.04503 0.03701 -0.0324 0.0631 1.0000
12.500 1.3347 0.04782 0.03987 -0.0321 0.0610 1.0000
12.750 1.3314 0.05084 0.04295 -0.0319 0.0590 1.0000
13.000 1.3259 0.05413 0.04631 -0.0318 0.0573 1.0000
13.250 1.3274 0.05671 0.04901 -0.0317 0.0558 1.0000
13.500 1.3294 0.05934 0.05175 -0.0317 0.0540 1.0000
13.750 1.3301 0.06219 0.05469 -0.0318 0.0523 1.0000
14.000 1.3301 0.06518 0.05776 -0.0320 0.0507 1.0000
14.250 1.3288 0.06838 0.06102 -0.0324 0.0491 1.0000
14.500 1.3252 0.07188 0.06455 -0.0328 0.0475 1.0000
14.750 1.3282 0.07464 0.06742 -0.0331 0.0459 1.0000
15.000 1.3311 0.07745 0.07036 -0.0335 0.0441 1.0000
15.250 1.3331 0.08044 0.07345 -0.0340 0.0421 1.0000
15.500 1.3334 0.08368 0.07676 -0.0346 0.0406 1.0000
15.750 1.3315 0.08722 0.08032 -0.0353 0.0391 1.0000
16.000 1.3347 0.09018 0.08342 -0.0360 0.0372 1.0000
16.250 1.3364 0.09333 0.08668 -0.0367 0.0355 1.0000
16.500 1.3367 0.09679 0.09022 -0.0376 0.0339 1.0000
16.750 1.3355 0.10047 0.09395 -0.0387 0.0327 1.0000
17.000 1.3365 0.10381 0.09740 -0.0396 0.0312 1.0000
17.250 1.3372 0.10728 0.10098 -0.0407 0.0295 1.0000
17.500 1.3367 0.11101 0.10479 -0.0420 0.0282 1.0000
17.750 1.3347 0.11502 0.10885 -0.0435 0.0271 1.0000
18.000 1.3353 0.11851 0.11245 -0.0447 0.0261 1.0000
18.250 1.3357 0.12210 0.11615 -0.0460 0.0249 1.0000
18.500 1.3352 0.12589 0.12004 -0.0475 0.0240 1.0000
18.750 1.3340 0.12986 0.12408 -0.0492 0.0232 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)