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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.16 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe238-il-1000000-n5.txt
Download as CSV file: xf-goe238-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2427   0.09873   0.09547  -0.0416   0.6103   0.0136
  -9.750  -0.2369   0.09575   0.09250  -0.0428   0.6058   0.0140
  -9.500  -0.2411   0.09067   0.08741  -0.0450   0.6021   0.0150
  -9.250  -0.2347   0.08815   0.08488  -0.0460   0.5971   0.0151
  -9.000  -0.2268   0.08600   0.08271  -0.0468   0.5926   0.0152
  -8.750  -0.2192   0.08381   0.08053  -0.0477   0.5878   0.0153
  -8.500  -0.2120   0.08166   0.07837  -0.0485   0.5828   0.0155
  -8.000  -0.2034   0.07684   0.07355  -0.0500   0.5734   0.0158
  -7.750  -0.2039   0.07434   0.07106  -0.0505   0.5692   0.0160
  -7.500  -0.2033   0.07190   0.06863  -0.0515   0.5643   0.0162
  -7.250  -0.1974   0.06892   0.06562  -0.0537   0.5600   0.0163
  -7.000  -0.1900   0.06558   0.06228  -0.0564   0.5558   0.0167
  -6.750  -0.1894   0.05821   0.05483  -0.0626   0.5531   0.0179
  -6.500  -0.1737   0.05588   0.05246  -0.0642   0.5483   0.0180
  -6.250  -0.1569   0.05346   0.04998  -0.0658   0.5439   0.0181
  -6.000  -0.1388   0.05100   0.04747  -0.0674   0.5400   0.0182
  -5.750  -0.1194   0.04880   0.04522  -0.0687   0.5354   0.0185
  -5.500  -0.0997   0.04609   0.04242  -0.0703   0.5310   0.0186
  -5.250  -0.0790   0.04335   0.03958  -0.0717   0.5271   0.0189
  -5.000  -0.0573   0.04044   0.03658  -0.0730   0.5233   0.0193
  -4.750  -0.0350   0.03712   0.03311  -0.0742   0.5193   0.0199
  -4.500  -0.0131   0.03236   0.02812  -0.0753   0.5154   0.0204
  -4.250   0.0024   0.02236   0.01745  -0.0754   0.5130   0.0213
  -4.000   0.0259   0.02044   0.01533  -0.0751   0.5091   0.0215
  -3.750   0.0506   0.01909   0.01380  -0.0747   0.5046   0.0218
  -3.500   0.0748   0.01740   0.01188  -0.0742   0.5002   0.0221
  -3.250   0.0997   0.01604   0.01030  -0.0737   0.4959   0.0225
  -3.000   0.1223   0.01304   0.00682  -0.0727   0.4929   0.0232
  -2.750   0.1483   0.01202   0.00560  -0.0723   0.4892   0.0236
  -2.500   0.1750   0.01139   0.00484  -0.0720   0.4852   0.0239
  -2.250   0.2019   0.01096   0.00430  -0.0717   0.4813   0.0242
  -2.000   0.2291   0.01069   0.00396  -0.0714   0.4773   0.0246
  -1.750   0.2565   0.01045   0.00365  -0.0711   0.4720   0.0248
  -1.500   0.2832   0.01007   0.00319  -0.0708   0.4663   0.0251
  -1.250   0.3100   0.00979   0.00287  -0.0705   0.4620   0.0255
  -1.000   0.3375   0.00962   0.00268  -0.0703   0.4590   0.0258
  -0.750   0.3649   0.00948   0.00253  -0.0700   0.4556   0.0262
  -0.500   0.3922   0.00936   0.00240  -0.0698   0.4518   0.0265
  -0.250   0.4194   0.00925   0.00226  -0.0695   0.4481   0.0269
   0.000   0.4468   0.00915   0.00215  -0.0693   0.4447   0.0273
   0.250   0.4742   0.00904   0.00203  -0.0691   0.4413   0.0278
   0.500   0.5015   0.00896   0.00193  -0.0688   0.4372   0.0283
   0.750   0.5287   0.00890   0.00185  -0.0686   0.4334   0.0287
   1.000   0.5560   0.00887   0.00181  -0.0684   0.4301   0.0291
   1.250   0.5834   0.00877   0.00173  -0.0681   0.4280   0.0302
   1.500   0.6109   0.00873   0.00171  -0.0680   0.4255   0.0311
   1.750   0.6384   0.00870   0.00169  -0.0678   0.4228   0.0320
   2.000   0.6658   0.00869   0.00168  -0.0676   0.4200   0.0330
   2.250   0.6931   0.00869   0.00168  -0.0674   0.4171   0.0339
   2.500   0.7203   0.00870   0.00169  -0.0672   0.4139   0.0356
   2.750   0.7479   0.00869   0.00172  -0.0671   0.4106   0.0379
   3.000   0.7751   0.00872   0.00175  -0.0669   0.4041   0.0411
   3.250   0.8021   0.00878   0.00181  -0.0667   0.3987   0.0460
   3.500   0.8294   0.00879   0.00186  -0.0665   0.3941   0.0518
   3.750   0.8565   0.00885   0.00192  -0.0663   0.3875   0.0577
   4.000   0.8834   0.00892   0.00199  -0.0661   0.3823   0.0656
   4.250   0.9104   0.00891   0.00207  -0.0660   0.3773   0.0971
   4.500   0.9366   0.00889   0.00220  -0.0657   0.3700   0.1995
   4.750   0.9905   0.00761   0.00252  -0.0722   0.3512   1.0000
   5.000   1.0150   0.00784   0.00266  -0.0716   0.3323   1.0000
   5.250   1.0330   0.00863   0.00310  -0.0701   0.2657   1.0000
   5.500   1.0542   0.00916   0.00346  -0.0690   0.2364   1.0000
   5.750   1.0776   0.00947   0.00371  -0.0683   0.2234   1.0000
   6.000   1.1013   0.00976   0.00395  -0.0676   0.2137   1.0000
   6.250   1.1255   0.01001   0.00417  -0.0670   0.2063   1.0000
   6.500   1.1493   0.01029   0.00442  -0.0664   0.1985   1.0000
   6.750   1.1735   0.01053   0.00463  -0.0658   0.1913   1.0000
   7.000   1.1969   0.01083   0.00490  -0.0651   0.1827   1.0000
   7.250   1.2194   0.01119   0.00519  -0.0643   0.1688   1.0000
   7.750   1.2453   0.01335   0.00677  -0.0602   0.0678   1.0000
   8.000   1.2661   0.01378   0.00718  -0.0592   0.0620   1.0000
   8.250   1.2868   0.01419   0.00759  -0.0582   0.0570   1.0000
   8.500   1.3082   0.01454   0.00795  -0.0573   0.0550   1.0000
   8.750   1.3282   0.01497   0.00837  -0.0562   0.0520   1.0000
   9.000   1.3474   0.01542   0.00882  -0.0551   0.0493   1.0000
   9.250   1.3663   0.01586   0.00928  -0.0539   0.0471   1.0000
   9.500   1.3860   0.01623   0.00968  -0.0528   0.0462   1.0000
   9.750   1.4043   0.01664   0.01012  -0.0515   0.0447   1.0000
  10.000   1.4211   0.01711   0.01061  -0.0501   0.0432   1.0000
  10.250   1.4340   0.01762   0.01115  -0.0479   0.0418   1.0000
  10.500   1.4441   0.01821   0.01175  -0.0454   0.0404   1.0000
  10.750   1.4542   0.01888   0.01245  -0.0432   0.0390   1.0000
  11.000   1.4664   0.01953   0.01315  -0.0415   0.0381   1.0000
  11.250   1.4773   0.02037   0.01403  -0.0400   0.0368   1.0000
  11.500   1.4873   0.02143   0.01514  -0.0389   0.0356   1.0000
  11.750   1.4967   0.02275   0.01650  -0.0382   0.0339   1.0000
  12.000   1.5058   0.02423   0.01800  -0.0376   0.0322   1.0000
  12.250   1.5165   0.02562   0.01945  -0.0373   0.0311   1.0000
  12.500   1.5256   0.02721   0.02107  -0.0369   0.0292   1.0000
  12.750   1.5321   0.02906   0.02295  -0.0365   0.0267   1.0000
  13.000   1.5385   0.03093   0.02485  -0.0362   0.0242   1.0000
  13.250   1.5424   0.03305   0.02700  -0.0358   0.0218   1.0000
  13.500   1.5452   0.03529   0.02927  -0.0354   0.0196   1.0000
  13.750   1.5465   0.03769   0.03170  -0.0350   0.0179   1.0000
  14.000   1.5480   0.04007   0.03414  -0.0347   0.0167   1.0000
  14.250   1.5479   0.04264   0.03676  -0.0343   0.0156   1.0000
  14.500   1.5474   0.04525   0.03942  -0.0340   0.0148   1.0000
  14.750   1.5475   0.04782   0.04205  -0.0338   0.0142   1.0000
  15.000   1.5472   0.05052   0.04482  -0.0336   0.0137   1.0000
  15.250   1.5452   0.05348   0.04784  -0.0335   0.0129   1.0000
  15.500   1.5446   0.05635   0.05077  -0.0336   0.0125   1.0000
  15.750   1.5429   0.05938   0.05386  -0.0336   0.0119   1.0000
  16.000   1.5420   0.06236   0.05692  -0.0337   0.0115   1.0000
  16.250   1.5415   0.06530   0.05992  -0.0339   0.0113   1.0000
  16.500   1.5404   0.06838   0.06306  -0.0341   0.0109   1.0000
  16.750   1.5382   0.07162   0.06637  -0.0344   0.0106   1.0000
  17.000   1.5361   0.07483   0.06965  -0.0347   0.0103   1.0000
  17.250   1.5321   0.07838   0.07327  -0.0351   0.0100   1.0000
  17.500   1.5283   0.08193   0.07689  -0.0356   0.0097   1.0000
  17.750   1.5240   0.08557   0.08060  -0.0362   0.0095   1.0000
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