GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 500,000 Max Cl/Cd: 110.04 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe238-il-500000-n5.txt Download as CSV file: xf-goe238-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2320 0.09681 0.09307 -0.0422 0.6485 0.0210
-9.250 -0.2300 0.09362 0.08986 -0.0440 0.6435 0.0211
-9.000 -0.2171 0.09130 0.08753 -0.0437 0.6372 0.0213
-8.750 -0.2074 0.08924 0.08544 -0.0441 0.6305 0.0216
-8.500 -0.1989 0.08714 0.08333 -0.0448 0.6248 0.0221
-8.250 -0.1923 0.08475 0.08093 -0.0457 0.6189 0.0228
-8.000 -0.1870 0.08225 0.07842 -0.0466 0.6136 0.0234
-7.750 -0.1885 0.07928 0.07545 -0.0484 0.6092 0.0245
-7.500 -0.1921 0.07660 0.07279 -0.0495 0.6047 0.0246
-7.250 -0.1876 0.07363 0.06981 -0.0519 0.5997 0.0247
-7.000 -0.1807 0.07031 0.06646 -0.0547 0.5953 0.0247
-6.750 -0.1720 0.06613 0.06223 -0.0592 0.5913 0.0248
-6.500 -0.1594 0.06250 0.05854 -0.0619 0.5867 0.0248
-6.250 -0.1452 0.05918 0.05516 -0.0639 0.5817 0.0248
-6.000 -0.1299 0.05610 0.05200 -0.0655 0.5771 0.0248
-5.500 -0.0975 0.05214 0.04799 -0.0664 0.5665 0.0255
-5.250 -0.0785 0.04952 0.04527 -0.0678 0.5617 0.0257
-5.000 -0.0579 0.04620 0.04184 -0.0698 0.5575 0.0257
-4.750 -0.0343 0.04463 0.04019 -0.0708 0.5526 0.0285
-4.250 0.0086 0.03828 0.03355 -0.0731 0.5442 0.0263
-4.000 0.0329 0.03376 0.02877 -0.0742 0.5406 0.0256
-3.750 0.0569 0.02995 0.02469 -0.0747 0.5366 0.0254
-3.500 0.0810 0.02827 0.02287 -0.0747 0.5322 0.0257
-3.000 0.1303 0.02407 0.01826 -0.0743 0.5242 0.0262
-2.750 0.1550 0.02149 0.01538 -0.0738 0.5199 0.0264
-2.500 0.1801 0.01957 0.01316 -0.0732 0.5156 0.0266
-2.000 0.2316 0.01661 0.00967 -0.0722 0.5078 0.0273
-1.750 0.2579 0.01533 0.00814 -0.0717 0.5039 0.0277
-1.500 0.2845 0.01422 0.00678 -0.0712 0.5001 0.0286
-1.250 0.3111 0.01342 0.00577 -0.0707 0.4965 0.0289
-1.000 0.3382 0.01288 0.00509 -0.0704 0.4928 0.0292
-0.750 0.3650 0.01231 0.00446 -0.0701 0.4881 0.0297
-0.500 0.3919 0.01202 0.00413 -0.0698 0.4831 0.0301
-0.250 0.4187 0.01180 0.00386 -0.0695 0.4787 0.0305
0.000 0.4459 0.01157 0.00362 -0.0692 0.4752 0.0311
0.250 0.4730 0.01135 0.00339 -0.0690 0.4717 0.0317
0.500 0.4999 0.01117 0.00318 -0.0686 0.4682 0.0324
0.750 0.5267 0.01104 0.00302 -0.0683 0.4649 0.0334
1.000 0.5536 0.01094 0.00289 -0.0680 0.4614 0.0342
1.250 0.5803 0.01073 0.00271 -0.0677 0.4575 0.0351
1.500 0.6072 0.01064 0.00264 -0.0674 0.4534 0.0361
1.750 0.6341 0.01059 0.00259 -0.0671 0.4499 0.0372
2.000 0.6609 0.01056 0.00255 -0.0668 0.4470 0.0386
2.250 0.6880 0.01052 0.00252 -0.0666 0.4445 0.0400
2.500 0.7151 0.01047 0.00253 -0.0664 0.4418 0.0426
2.750 0.7423 0.01047 0.00256 -0.0662 0.4389 0.0460
3.000 0.7692 0.01047 0.00257 -0.0659 0.4355 0.0498
3.250 0.7960 0.01051 0.00261 -0.0657 0.4321 0.0549
3.500 0.8228 0.01054 0.00266 -0.0654 0.4290 0.0626
4.000 0.8756 0.01042 0.00283 -0.0649 0.4184 0.1952
4.500 0.9546 0.00909 0.00316 -0.0705 0.4057 1.0000
4.750 0.9800 0.00923 0.00327 -0.0700 0.4003 1.0000
5.000 1.0058 0.00936 0.00339 -0.0696 0.3952 1.0000
5.250 1.0313 0.00949 0.00351 -0.0692 0.3869 1.0000
5.500 1.0565 0.00965 0.00364 -0.0687 0.3780 1.0000
5.750 1.0813 0.00984 0.00380 -0.0681 0.3661 1.0000
6.000 1.1059 0.01005 0.00396 -0.0676 0.3514 1.0000
6.250 1.1297 0.01033 0.00417 -0.0669 0.3300 1.0000
6.500 1.1497 0.01091 0.00454 -0.0658 0.2864 1.0000
7.000 1.1882 0.01223 0.00554 -0.0634 0.2312 1.0000
7.250 1.2096 0.01270 0.00597 -0.0625 0.2185 1.0000
7.500 1.2311 0.01314 0.00637 -0.0616 0.2071 1.0000
7.750 1.2524 0.01358 0.00679 -0.0607 0.1982 1.0000
8.000 1.2743 0.01395 0.00716 -0.0599 0.1888 1.0000
8.250 1.2951 0.01439 0.00759 -0.0590 0.1775 1.0000
8.500 1.3136 0.01498 0.00809 -0.0578 0.1572 1.0000
8.750 1.3106 0.01696 0.00956 -0.0539 0.0795 1.0000
9.000 1.3228 0.01780 0.01035 -0.0518 0.0680 1.0000
9.250 1.3372 0.01845 0.01102 -0.0501 0.0637 1.0000
9.500 1.3473 0.01918 0.01177 -0.0477 0.0597 1.0000
9.750 1.3554 0.01993 0.01255 -0.0450 0.0567 1.0000
10.000 1.3655 0.02064 0.01333 -0.0429 0.0549 1.0000
10.250 1.3739 0.02156 0.01429 -0.0409 0.0530 1.0000
10.500 1.3804 0.02277 0.01556 -0.0393 0.0513 1.0000
10.750 1.3864 0.02426 0.01710 -0.0382 0.0495 1.0000
11.000 1.3918 0.02596 0.01887 -0.0373 0.0479 1.0000
11.250 1.3996 0.02754 0.02052 -0.0367 0.0467 1.0000
11.500 1.4085 0.02907 0.02212 -0.0361 0.0457 1.0000
11.750 1.4166 0.03070 0.02382 -0.0356 0.0444 1.0000
12.000 1.4232 0.03250 0.02568 -0.0351 0.0430 1.0000
12.250 1.4283 0.03447 0.02771 -0.0346 0.0417 1.0000
12.500 1.4314 0.03663 0.02992 -0.0342 0.0404 1.0000
12.750 1.4331 0.03900 0.03233 -0.0337 0.0389 1.0000
13.000 1.4387 0.04095 0.03437 -0.0334 0.0381 1.0000
13.250 1.4442 0.04293 0.03642 -0.0330 0.0364 1.0000
13.500 1.4475 0.04516 0.03871 -0.0328 0.0347 1.0000
13.750 1.4490 0.04760 0.04120 -0.0325 0.0333 1.0000
14.000 1.4499 0.05014 0.04379 -0.0323 0.0321 1.0000
14.250 1.4531 0.05248 0.04621 -0.0321 0.0305 1.0000
14.500 1.4552 0.05502 0.04881 -0.0321 0.0288 1.0000
14.750 1.4559 0.05779 0.05160 -0.0322 0.0268 1.0000
15.000 1.4574 0.06051 0.05439 -0.0323 0.0249 1.0000
15.250 1.4576 0.06341 0.05734 -0.0325 0.0232 1.0000
15.500 1.4571 0.06647 0.06045 -0.0328 0.0218 1.0000
15.750 1.4566 0.06955 0.06359 -0.0331 0.0204 1.0000
16.000 1.4541 0.07295 0.06703 -0.0335 0.0188 1.0000
16.250 1.4524 0.07629 0.07044 -0.0340 0.0182 1.0000
16.500 1.4510 0.07964 0.07387 -0.0346 0.0172 1.0000
16.750 1.4487 0.08318 0.07748 -0.0352 0.0166 1.0000
17.000 1.4462 0.08676 0.08114 -0.0359 0.0159 1.0000
17.250 1.4415 0.09074 0.08518 -0.0369 0.0153 1.0000
17.500 1.4376 0.09466 0.08918 -0.0378 0.0148 1.0000
17.750 1.4350 0.09844 0.09306 -0.0388 0.0144 1.0000
18.000 1.4323 0.10227 0.09697 -0.0399 0.0140 1.0000
18.250 1.4292 0.10620 0.10099 -0.0411 0.0136 1.0000
18.500 1.4250 0.11038 0.10526 -0.0425 0.0132 1.0000
18.750 1.4209 0.11461 0.10957 -0.0439 0.0128 1.0000
19.000 1.4158 0.11905 0.11409 -0.0456 0.0125 1.0000
19.250 1.4092 0.12379 0.11891 -0.0475 0.0122 1.0000
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Polar data table (+)
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