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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)
Reynolds number: 100,000
Max Cl/Cd: 55.12 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe238-il-100000-n5.txt
Download as CSV file: xf-goe238-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2125   0.09836   0.09297  -0.0390   0.7934   0.0523
  -8.500  -0.2061   0.09583   0.09038  -0.0409   0.7802   0.0535
  -8.250  -0.2036   0.09373   0.08825  -0.0435   0.7681   0.0546
  -8.000  -0.2041   0.09182   0.08633  -0.0464   0.7573   0.0550
  -7.750  -0.2059   0.08993   0.08442  -0.0500   0.7476   0.0552
  -7.500  -0.1999   0.08723   0.08169  -0.0541   0.7385   0.0554
  -7.250  -0.1839   0.08294   0.07737  -0.0507   0.7307   0.0561
  -7.000  -0.1707   0.07995   0.07436  -0.0500   0.7223   0.0574
  -6.750  -0.1603   0.07735   0.07172  -0.0511   0.7148   0.0592
  -6.500  -0.1504   0.07473   0.06907  -0.0533   0.7073   0.0611
  -6.250  -0.1393   0.07214   0.06641  -0.0569   0.7000   0.0631
  -6.000  -0.1227   0.06974   0.06378  -0.0641   0.6937   0.0644
  -5.750  -0.1075   0.06638   0.06036  -0.0660   0.6864   0.0648
  -5.500  -0.0944   0.06322   0.05719  -0.0650   0.6804   0.0655
  -5.250  -0.0792   0.06058   0.05452  -0.0650   0.6738   0.0667
  -5.000  -0.0618   0.05808   0.05195  -0.0659   0.6673   0.0684
  -4.750  -0.0315   0.05620   0.04957  -0.0718   0.6622   0.0745
  -4.500  -0.0174   0.05277   0.04624  -0.0712   0.6558   0.0756
  -4.250  -0.0002   0.05042   0.04389  -0.0709   0.6497   0.0775
  -4.000   0.0209   0.04824   0.04155  -0.0715   0.6448   0.0802
  -3.750   0.0493   0.04597   0.03892  -0.0742   0.6385   0.0862
  -3.500   0.0683   0.04366   0.03661  -0.0739   0.6329   0.0879
  -3.250   0.0905   0.04179   0.03460  -0.0740   0.6284   0.0912
  -3.000   0.1157   0.03991   0.03250  -0.0749   0.6229   0.0995
  -2.750   0.1384   0.03823   0.03075  -0.0749   0.6175   0.1035
  -2.250   0.1996   0.03228   0.02378  -0.0753   0.6091   0.0627
  -1.750   0.2543   0.02850   0.01914  -0.0745   0.5990   0.0550
  -1.500   0.2801   0.02716   0.01757  -0.0742   0.5951   0.0545
  -1.250   0.3064   0.02602   0.01622  -0.0738   0.5905   0.0542
  -1.000   0.3332   0.02506   0.01499  -0.0735   0.5858   0.0544
  -0.750   0.3602   0.02426   0.01388  -0.0730   0.5818   0.0559
  -0.500   0.3866   0.02344   0.01298  -0.0728   0.5785   0.0572
  -0.250   0.4135   0.02278   0.01217  -0.0725   0.5743   0.0575
   0.000   0.4403   0.02220   0.01149  -0.0721   0.5696   0.0578
   0.250   0.4672   0.02168   0.01085  -0.0717   0.5656   0.0584
   0.500   0.4943   0.02121   0.01027  -0.0713   0.5624   0.0593
   0.750   0.5210   0.02088   0.00988  -0.0709   0.5590   0.0610
   1.000   0.5473   0.02074   0.00971  -0.0706   0.5549   0.0640
   1.250   0.5731   0.02038   0.00942  -0.0702   0.5513   0.0663
   1.500   0.5991   0.02012   0.00918  -0.0697   0.5483   0.0684
   1.750   0.6260   0.01994   0.00896  -0.0693   0.5457   0.0709
   2.000   0.6524   0.01993   0.00890  -0.0689   0.5422   0.0746
   2.250   0.6778   0.01988   0.00891  -0.0686   0.5376   0.0816
   2.500   0.7040   0.01984   0.00886  -0.0682   0.5335   0.0891
   2.750   0.7307   0.01975   0.00884  -0.0679   0.5301   0.1092
   3.250   0.8021   0.01838   0.00925  -0.0713   0.5206   1.0000
   3.500   0.8272   0.01861   0.00940  -0.0708   0.5166   1.0000
   3.750   0.8532   0.01879   0.00947  -0.0703   0.5132   1.0000
   4.000   0.8779   0.01908   0.00972  -0.0697   0.5092   1.0000
   4.250   0.9015   0.01943   0.01013  -0.0691   0.5042   1.0000
   4.500   0.9264   0.01969   0.01037  -0.0686   0.5002   1.0000
   4.750   0.9523   0.01987   0.01050  -0.0681   0.4968   1.0000
   5.000   0.9761   0.02018   0.01086  -0.0675   0.4919   1.0000
   5.250   0.9994   0.02048   0.01121  -0.0668   0.4860   1.0000
   5.500   1.0250   0.02061   0.01132  -0.0663   0.4814   1.0000
   5.750   1.0496   0.02087   0.01161  -0.0657   0.4770   1.0000
   6.000   1.0717   0.02133   0.01220  -0.0650   0.4717   1.0000
   6.250   1.0960   0.02155   0.01247  -0.0644   0.4668   1.0000
   6.500   1.1219   0.02163   0.01253  -0.0639   0.4619   1.0000
   6.750   1.1422   0.02204   0.01312  -0.0629   0.4537   1.0000
   7.000   1.1683   0.02191   0.01294  -0.0622   0.4465   1.0000
   7.250   1.1876   0.02227   0.01348  -0.0611   0.4362   1.0000
   7.500   1.2107   0.02235   0.01361  -0.0602   0.4275   1.0000
   7.750   1.2312   0.02265   0.01402  -0.0592   0.4180   1.0000
   8.000   1.2518   0.02294   0.01443  -0.0581   0.4086   1.0000
   8.250   1.2732   0.02310   0.01464  -0.0571   0.3985   1.0000
   8.500   1.2906   0.02357   0.01528  -0.0557   0.3858   1.0000
   8.750   1.3079   0.02401   0.01586  -0.0544   0.3730   1.0000
   9.000   1.3240   0.02450   0.01645  -0.0529   0.3590   1.0000
   9.250   1.3382   0.02505   0.01707  -0.0512   0.3418   1.0000
   9.500   1.3498   0.02567   0.01773  -0.0492   0.3208   1.0000
   9.750   1.3584   0.02647   0.01850  -0.0470   0.2995   1.0000
  10.000   1.3615   0.02746   0.01942  -0.0441   0.2822   1.0000
  10.250   1.3595   0.02882   0.02070  -0.0410   0.2672   1.0000
  10.500   1.3540   0.03070   0.02252  -0.0385   0.2529   1.0000
  10.750   1.3489   0.03295   0.02475  -0.0369   0.2405   1.0000
  11.000   1.3427   0.03553   0.02730  -0.0356   0.2278   1.0000
  11.250   1.3355   0.03837   0.03013  -0.0346   0.2149   1.0000
  11.500   1.3304   0.04123   0.03303  -0.0339   0.2019   1.0000
  11.750   1.3256   0.04420   0.03608  -0.0334   0.1879   1.0000
  12.000   1.3192   0.04744   0.03936  -0.0331   0.1707   1.0000
  12.250   1.3108   0.05099   0.04290  -0.0329   0.1459   1.0000
  12.500   1.2965   0.05523   0.04697  -0.0329   0.1224   1.0000
  12.750   1.2840   0.05939   0.05099  -0.0330   0.1078   1.0000
  13.000   1.2747   0.06327   0.05480  -0.0331   0.0987   1.0000
  13.250   1.2674   0.06710   0.05859  -0.0334   0.0924   1.0000
  13.500   1.2638   0.07058   0.06211  -0.0336   0.0875   1.0000
  13.750   1.2600   0.07416   0.06572  -0.0340   0.0833   1.0000
  14.000   1.2546   0.07797   0.06953  -0.0344   0.0798   1.0000
  14.250   1.2552   0.08109   0.07276  -0.0348   0.0761   1.0000
  14.500   1.2546   0.08438   0.07613  -0.0352   0.0727   1.0000
  14.750   1.2528   0.08780   0.07956  -0.0357   0.0695   1.0000
  15.000   1.2546   0.09069   0.08249  -0.0359   0.0667   1.0000
  15.250   1.2571   0.09365   0.08558  -0.0363   0.0636   1.0000
  15.500   1.2597   0.09651   0.08851  -0.0367   0.0609   1.0000
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