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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
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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