GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.61 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe238-il-1000000.txt Download as CSV file: xf-goe238-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2233 0.09660 0.09366 -0.0437 0.6693 0.0199
-9.250 -0.2242 0.09337 0.09041 -0.0459 0.6633 0.0200
-9.000 -0.2217 0.09038 0.08742 -0.0475 0.6575 0.0200
-8.750 -0.2130 0.08679 0.08382 -0.0475 0.6510 0.0202
-8.500 -0.2046 0.08442 0.08141 -0.0478 0.6444 0.0203
-8.250 -0.1968 0.08215 0.07914 -0.0483 0.6381 0.0204
-8.000 -0.1896 0.08004 0.07702 -0.0488 0.6315 0.0207
-7.750 -0.1848 0.07782 0.07478 -0.0493 0.6259 0.0209
-7.500 -0.1824 0.07555 0.07253 -0.0497 0.6204 0.0211
-7.250 -0.1823 0.07333 0.07031 -0.0502 0.6149 0.0213
-7.000 -0.1754 0.07075 0.06770 -0.0520 0.6096 0.0218
-6.750 -0.1667 0.06788 0.06482 -0.0543 0.6047 0.0224
-6.500 -0.1563 0.06285 0.05972 -0.0615 0.6004 0.0235
-6.250 -0.1416 0.05896 0.05575 -0.0647 0.5955 0.0236
-6.000 -0.1313 0.05454 0.05127 -0.0666 0.5912 0.0238
-5.750 -0.1154 0.05233 0.04904 -0.0671 0.5859 0.0239
-5.500 -0.0979 0.05017 0.04682 -0.0678 0.5804 0.0241
-5.250 -0.0790 0.04804 0.04463 -0.0687 0.5753 0.0243
-5.000 -0.0588 0.04577 0.04230 -0.0698 0.5703 0.0246
-4.750 -0.0377 0.04344 0.03988 -0.0708 0.5648 0.0250
-4.500 -0.0155 0.04103 0.03738 -0.0719 0.5598 0.0257
-4.250 0.0171 0.03611 0.03216 -0.0740 0.5560 0.0276
-4.000 0.0350 0.03159 0.02745 -0.0745 0.5517 0.0280
-3.750 0.0570 0.03014 0.02592 -0.0745 0.5466 0.0282
-3.500 0.0803 0.02880 0.02450 -0.0745 0.5421 0.0285
-3.250 0.1044 0.02739 0.02300 -0.0745 0.5374 0.0288
-3.000 0.1289 0.02587 0.02137 -0.0744 0.5326 0.0294
-2.750 0.1575 0.02349 0.01864 -0.0736 0.5281 0.0321
-2.500 0.1799 0.02003 0.01478 -0.0729 0.5248 0.0326
-2.250 0.2046 0.01881 0.01351 -0.0727 0.5201 0.0330
-2.000 0.2299 0.01796 0.01258 -0.0724 0.5151 0.0334
-1.750 0.2558 0.01721 0.01173 -0.0721 0.5102 0.0341
-1.500 0.2823 0.01639 0.01081 -0.0718 0.5057 0.0352
-1.250 0.3115 0.01664 0.01078 -0.0711 0.5010 0.0376
-1.000 0.3349 0.01288 0.00659 -0.0699 0.4968 0.0319
-0.750 0.3617 0.01191 0.00547 -0.0695 0.4927 0.0318
-0.500 0.3890 0.01134 0.00479 -0.0692 0.4883 0.0321
-0.250 0.4163 0.01097 0.00432 -0.0688 0.4842 0.0323
0.000 0.4423 0.01010 0.00336 -0.0684 0.4803 0.0328
0.250 0.4694 0.00974 0.00301 -0.0681 0.4774 0.0334
0.500 0.4966 0.00953 0.00281 -0.0678 0.4742 0.0339
0.750 0.5237 0.00935 0.00262 -0.0676 0.4708 0.0346
1.000 0.5507 0.00921 0.00247 -0.0672 0.4674 0.0353
1.250 0.5776 0.00914 0.00237 -0.0669 0.4636 0.0364
1.500 0.6052 0.00904 0.00229 -0.0667 0.4605 0.0374
1.750 0.6319 0.00883 0.00208 -0.0664 0.4569 0.0387
2.000 0.6590 0.00876 0.00201 -0.0661 0.4536 0.0401
2.250 0.6860 0.00875 0.00200 -0.0659 0.4501 0.0419
2.500 0.7133 0.00875 0.00200 -0.0657 0.4472 0.0437
2.750 0.7406 0.00866 0.00195 -0.0655 0.4448 0.0472
3.000 0.7682 0.00866 0.00197 -0.0653 0.4418 0.0512
3.250 0.7952 0.00863 0.00195 -0.0651 0.4369 0.0576
3.500 0.8219 0.00867 0.00198 -0.0648 0.4326 0.0667
3.750 0.8489 0.00855 0.00204 -0.0646 0.4301 0.1493
4.000 0.9094 0.00695 0.00227 -0.0725 0.4237 1.0000
4.250 0.9351 0.00706 0.00234 -0.0720 0.4188 1.0000
4.500 0.9612 0.00715 0.00242 -0.0716 0.4144 1.0000
4.750 0.9875 0.00722 0.00249 -0.0712 0.4099 1.0000
5.000 1.0133 0.00733 0.00257 -0.0708 0.4047 1.0000
5.250 1.0391 0.00744 0.00267 -0.0704 0.3988 1.0000
5.500 1.0652 0.00753 0.00276 -0.0700 0.3923 1.0000
5.750 1.0905 0.00769 0.00288 -0.0695 0.3854 1.0000
6.000 1.1166 0.00778 0.00299 -0.0692 0.3780 1.0000
6.250 1.1417 0.00795 0.00312 -0.0687 0.3663 1.0000
6.500 1.1665 0.00815 0.00327 -0.0682 0.3508 1.0000
6.750 1.1887 0.00856 0.00352 -0.0673 0.3160 1.0000
7.000 1.2041 0.00955 0.00414 -0.0655 0.2521 1.0000
7.250 1.2250 0.01007 0.00455 -0.0644 0.2305 1.0000
7.500 1.2473 0.01046 0.00489 -0.0636 0.2177 1.0000
7.750 1.2694 0.01086 0.00524 -0.0628 0.2064 1.0000
8.000 1.2913 0.01127 0.00560 -0.0619 0.1922 1.0000
8.250 1.3120 0.01176 0.00598 -0.0609 0.1702 1.0000
8.500 1.3132 0.01366 0.00730 -0.0573 0.0810 1.0000
8.750 1.3281 0.01447 0.00802 -0.0555 0.0644 1.0000
9.000 1.3475 0.01493 0.00849 -0.0544 0.0603 1.0000
9.250 1.3655 0.01546 0.00903 -0.0530 0.0570 1.0000
9.500 1.3821 0.01604 0.00961 -0.0515 0.0535 1.0000
9.750 1.4006 0.01647 0.01008 -0.0502 0.0522 1.0000
10.000 1.4183 0.01691 0.01057 -0.0489 0.0508 1.0000
10.250 1.4329 0.01744 0.01112 -0.0471 0.0489 1.0000
10.500 1.4423 0.01805 0.01176 -0.0445 0.0472 1.0000
10.750 1.4490 0.01885 0.01259 -0.0417 0.0451 1.0000
11.000 1.4581 0.01965 0.01345 -0.0396 0.0438 1.0000
11.250 1.4709 0.02037 0.01422 -0.0383 0.0428 1.0000
11.500 1.4820 0.02135 0.01525 -0.0372 0.0415 1.0000
11.750 1.4919 0.02260 0.01653 -0.0364 0.0397 1.0000
12.000 1.4996 0.02420 0.01816 -0.0359 0.0378 1.0000
12.250 1.5085 0.02578 0.01980 -0.0355 0.0363 1.0000
12.500 1.5205 0.02708 0.02115 -0.0352 0.0347 1.0000
12.750 1.5293 0.02872 0.02281 -0.0349 0.0327 1.0000
13.000 1.5346 0.03071 0.02481 -0.0345 0.0302 1.0000
13.250 1.5422 0.03247 0.02663 -0.0342 0.0285 1.0000
13.500 1.5460 0.03461 0.02880 -0.0338 0.0266 1.0000
13.750 1.5483 0.03691 0.03113 -0.0335 0.0245 1.0000
14.000 1.5506 0.03922 0.03349 -0.0332 0.0230 1.0000
14.250 1.5488 0.04195 0.03625 -0.0328 0.0214 1.0000
14.500 1.5479 0.04463 0.03899 -0.0325 0.0206 1.0000
14.750 1.5480 0.04720 0.04163 -0.0323 0.0197 1.0000
15.000 1.5457 0.05009 0.04457 -0.0321 0.0188 1.0000
15.250 1.5431 0.05313 0.04767 -0.0320 0.0181 1.0000
15.500 1.5373 0.05661 0.05121 -0.0321 0.0173 1.0000
15.750 1.5367 0.05953 0.05421 -0.0322 0.0169 1.0000
16.000 1.5350 0.06261 0.05737 -0.0323 0.0165 1.0000
16.250 1.5326 0.06584 0.06067 -0.0325 0.0160 1.0000
16.500 1.5306 0.06904 0.06393 -0.0328 0.0156 1.0000
16.750 1.5268 0.07251 0.06747 -0.0332 0.0152 1.0000
17.000 1.5207 0.07629 0.07132 -0.0336 0.0148 1.0000
17.250 1.5138 0.08026 0.07537 -0.0342 0.0145 1.0000
17.500 1.5025 0.08491 0.08008 -0.0350 0.0140 1.0000
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Polar data table (+)
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