GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 500,000 Max Cl/Cd: 117.06 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe238-il-500000.txt Download as CSV file: xf-goe238-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1948 0.08867 0.08519 -0.0444 0.6940 0.0263
-8.250 -0.1907 0.08598 0.08251 -0.0459 0.6868 0.0271
-8.000 -0.1999 0.08361 0.08014 -0.0491 0.6804 0.0275
-7.750 -0.2058 0.08109 0.07763 -0.0512 0.6742 0.0276
-7.500 -0.2009 0.07776 0.07428 -0.0549 0.6678 0.0276
-7.250 -0.1924 0.07431 0.07080 -0.0543 0.6619 0.0278
-7.000 -0.1804 0.07181 0.06829 -0.0535 0.6554 0.0280
-6.750 -0.1693 0.06939 0.06583 -0.0540 0.6488 0.0283
-6.500 -0.1580 0.06699 0.06339 -0.0551 0.6429 0.0287
-6.250 -0.1454 0.06437 0.06076 -0.0568 0.6369 0.0291
-6.000 -0.1317 0.06165 0.05798 -0.0588 0.6311 0.0297
-5.750 -0.1164 0.05878 0.05504 -0.0610 0.6257 0.0306
-5.500 -0.0882 0.05417 0.05021 -0.0683 0.6208 0.0322
-4.750 -0.0375 0.04548 0.04132 -0.0704 0.6049 0.0330
-4.500 -0.0179 0.04356 0.03933 -0.0707 0.5993 0.0335
-4.250 0.0035 0.04147 0.03712 -0.0714 0.5943 0.0341
-4.000 0.0268 0.03918 0.03474 -0.0722 0.5891 0.0351
-3.750 0.0630 0.03550 0.03051 -0.0737 0.5844 0.0377
-3.500 0.0808 0.03219 0.02716 -0.0739 0.5796 0.0382
-3.250 0.1027 0.03067 0.02559 -0.0739 0.5745 0.0386
-3.000 0.1259 0.02924 0.02411 -0.0739 0.5692 0.0391
-2.750 0.1500 0.02785 0.02259 -0.0738 0.5644 0.0400
-2.500 0.1756 0.02635 0.02090 -0.0736 0.5600 0.0420
-2.250 0.2034 0.02352 0.01758 -0.0728 0.5558 0.0447
-2.000 0.2277 0.02219 0.01623 -0.0727 0.5511 0.0454
-1.750 0.2527 0.02119 0.01514 -0.0725 0.5468 0.0463
-1.500 0.2786 0.02023 0.01404 -0.0722 0.5426 0.0480
-1.250 0.3089 0.02084 0.01422 -0.0712 0.5381 0.0516
-1.000 0.3320 0.01791 0.01124 -0.0711 0.5339 0.0533
-0.750 0.3580 0.01712 0.01036 -0.0709 0.5295 0.0546
-0.500 0.3849 0.01654 0.00969 -0.0705 0.5249 0.0575
-0.250 0.4120 0.01579 0.00872 -0.0701 0.5206 0.0623
0.000 0.4386 0.01504 0.00795 -0.0698 0.5163 0.0643
0.250 0.4657 0.01469 0.00744 -0.0694 0.5120 0.0678
0.500 0.4926 0.01393 0.00664 -0.0692 0.5081 0.0743
0.750 0.5200 0.01343 0.00610 -0.0689 0.5043 0.0772
1.000 0.5496 0.01203 0.00431 -0.0675 0.5012 0.0460
1.250 0.5765 0.01183 0.00409 -0.0672 0.4979 0.0474
1.500 0.6033 0.01159 0.00385 -0.0669 0.4949 0.0482
1.750 0.6302 0.01136 0.00365 -0.0665 0.4915 0.0494
2.000 0.6571 0.01121 0.00350 -0.0662 0.4880 0.0508
2.250 0.6835 0.01100 0.00330 -0.0658 0.4847 0.0527
2.500 0.7099 0.01092 0.00323 -0.0655 0.4814 0.0563
2.750 0.7368 0.01090 0.00322 -0.0652 0.4781 0.0601
3.000 0.7634 0.01074 0.00313 -0.0648 0.4748 0.0656
3.250 0.7903 0.01068 0.00309 -0.0646 0.4717 0.0747
3.500 0.8161 0.01046 0.00315 -0.0642 0.4685 0.2041
3.750 0.8732 0.00902 0.00334 -0.0710 0.4640 1.0000
4.000 0.8992 0.00907 0.00341 -0.0706 0.4603 1.0000
4.250 0.9252 0.00915 0.00349 -0.0701 0.4562 1.0000
4.500 0.9508 0.00924 0.00355 -0.0696 0.4514 1.0000
4.750 0.9764 0.00937 0.00364 -0.0691 0.4462 1.0000
5.000 1.0023 0.00943 0.00373 -0.0687 0.4414 1.0000
5.250 1.0280 0.00953 0.00383 -0.0683 0.4365 1.0000
5.500 1.0534 0.00968 0.00395 -0.0678 0.4316 1.0000
5.750 1.0793 0.00975 0.00407 -0.0674 0.4263 1.0000
6.000 1.1048 0.00986 0.00419 -0.0669 0.4204 1.0000
6.250 1.1302 0.00999 0.00432 -0.0665 0.4143 1.0000
6.500 1.1557 0.01008 0.00445 -0.0661 0.4063 1.0000
6.750 1.1807 0.01024 0.00460 -0.0656 0.3990 1.0000
7.000 1.2060 0.01036 0.00477 -0.0651 0.3899 1.0000
7.250 1.2308 0.01052 0.00494 -0.0646 0.3791 1.0000
7.500 1.2549 0.01072 0.00513 -0.0640 0.3632 1.0000
7.750 1.2775 0.01103 0.00538 -0.0632 0.3387 1.0000
8.000 1.2947 0.01176 0.00584 -0.0618 0.2863 1.0000
8.250 1.3094 0.01271 0.00656 -0.0600 0.2489 1.0000
8.500 1.3271 0.01341 0.00717 -0.0586 0.2295 1.0000
8.750 1.3448 0.01409 0.00778 -0.0573 0.2123 1.0000
9.000 1.3604 0.01488 0.00846 -0.0557 0.1909 1.0000
9.250 1.3728 0.01584 0.00921 -0.0537 0.1484 1.0000
9.500 1.3651 0.01793 0.01084 -0.0492 0.0823 1.0000
9.750 1.3713 0.01895 0.01182 -0.0464 0.0723 1.0000
10.000 1.3761 0.01984 0.01273 -0.0432 0.0683 1.0000
10.250 1.3782 0.02098 0.01391 -0.0402 0.0647 1.0000
10.500 1.3827 0.02220 0.01519 -0.0381 0.0623 1.0000
10.750 1.3892 0.02354 0.01663 -0.0367 0.0605 1.0000
11.000 1.3940 0.02523 0.01839 -0.0358 0.0584 1.0000
11.250 1.3971 0.02722 0.02044 -0.0350 0.0565 1.0000
11.500 1.3963 0.02967 0.02294 -0.0342 0.0544 1.0000
11.750 1.3959 0.03213 0.02550 -0.0335 0.0527 1.0000
12.000 1.4036 0.03385 0.02730 -0.0331 0.0513 1.0000
12.250 1.4091 0.03580 0.02932 -0.0327 0.0495 1.0000
12.500 1.4118 0.03804 0.03162 -0.0322 0.0477 1.0000
12.750 1.4104 0.04073 0.03435 -0.0318 0.0462 1.0000
13.000 1.4019 0.04416 0.03784 -0.0314 0.0444 1.0000
13.250 1.4078 0.04616 0.03992 -0.0311 0.0430 1.0000
13.500 1.4132 0.04821 0.04205 -0.0309 0.0412 1.0000
13.750 1.4161 0.05055 0.04445 -0.0307 0.0394 1.0000
14.000 1.4131 0.05360 0.04753 -0.0306 0.0377 1.0000
14.250 1.4115 0.05662 0.05061 -0.0306 0.0360 1.0000
14.500 1.4168 0.05889 0.05297 -0.0307 0.0343 1.0000
14.750 1.4198 0.06149 0.05560 -0.0308 0.0326 1.0000
15.000 1.4162 0.06490 0.05904 -0.0311 0.0310 1.0000
15.250 1.4148 0.06809 0.06231 -0.0314 0.0298 1.0000
15.500 1.4164 0.07098 0.06528 -0.0317 0.0285 1.0000
15.750 1.4183 0.07384 0.06820 -0.0321 0.0272 1.0000
16.000 1.4157 0.07734 0.07173 -0.0326 0.0263 1.0000
16.250 1.4077 0.08158 0.07601 -0.0333 0.0253 1.0000
16.500 1.4097 0.08455 0.07907 -0.0339 0.0246 1.0000
16.750 1.4101 0.08779 0.08241 -0.0345 0.0236 1.0000
17.000 1.4092 0.09121 0.08589 -0.0352 0.0229 1.0000
17.250 1.4077 0.09480 0.08956 -0.0361 0.0223 1.0000
17.500 1.4048 0.09861 0.09340 -0.0371 0.0216 1.0000
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