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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
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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