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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.1 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe314-il-1000000.txt
Download as CSV file: xf-goe314-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 314 (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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3256   0.09037   0.08878  -0.0226   1.0000   0.0197
  -8.000  -0.3316   0.08784   0.08628  -0.0229   1.0000   0.0198
  -7.750  -0.3460   0.08573   0.08421  -0.0220   1.0000   0.0198
  -7.500  -0.3229   0.08023   0.07870  -0.0310   0.9972   0.0199
  -7.250  -0.3050   0.07574   0.07421  -0.0337   0.9940   0.0202
  -6.250  -0.2030   0.06186   0.06023  -0.0544   0.9590   0.0225
  -6.000  -0.1409   0.05362   0.05176  -0.0725   0.9430   0.0238
  -5.250  -0.0643   0.04374   0.04141  -0.0819   0.8557   0.0246
  -5.000  -0.0457   0.04183   0.03936  -0.0822   0.8365   0.0250
  -4.750  -0.0259   0.03981   0.03721  -0.0825   0.8201   0.0256
  -4.500   0.0031   0.03676   0.03389  -0.0836   0.8059   0.0281
  -4.250   0.0257   0.03414   0.03108  -0.0835   0.7927   0.0283
  -4.000   0.0423   0.02948   0.02616  -0.0834   0.7804   0.0286
  -3.750   0.0629   0.02797   0.02454  -0.0830   0.7668   0.0289
  -3.500   0.0848   0.02672   0.02318  -0.0826   0.7520   0.0292
  -3.250   0.1074   0.02548   0.02182  -0.0821   0.7358   0.0295
  -3.000   0.1306   0.02425   0.02045  -0.0816   0.7184   0.0301
  -2.750   0.1544   0.02298   0.01902  -0.0810   0.6989   0.0312
  -2.500   0.1832   0.02154   0.01720  -0.0796   0.6772   0.0336
  -2.250   0.2062   0.01985   0.01521  -0.0786   0.6518   0.0337
  -1.500  -0.1181   0.01499   0.01176   0.0201   0.6060   0.0336
  -1.000   0.3223   0.01207   0.00595  -0.0739   0.5162   0.0329
  -0.750   0.3477   0.01143   0.00508  -0.0732   0.4954   0.0332
  -0.500   0.3737   0.01112   0.00462  -0.0726   0.4768   0.0335
  -0.250   0.3997   0.01073   0.00409  -0.0721   0.4612   0.0338
   0.000   0.4249   0.00998   0.00320  -0.0714   0.4473   0.0342
   0.500   0.4772   0.00955   0.00271  -0.0705   0.4261   0.0359
   0.750   0.5035   0.00947   0.00260  -0.0701   0.4173   0.0370
   1.000   0.5299   0.00934   0.00244  -0.0697   0.4091   0.0380
   1.250   0.5561   0.00926   0.00232  -0.0692   0.4012   0.0389
   1.500   0.5827   0.00921   0.00224  -0.0688   0.3928   0.0398
   1.750   0.6085   0.00909   0.00208  -0.0683   0.3832   0.0408
   2.000   0.6345   0.00899   0.00196  -0.0678   0.3739   0.0429
   2.250   0.6611   0.00899   0.00195  -0.0675   0.3664   0.0451
   2.500   0.6875   0.00903   0.00196  -0.0671   0.3579   0.0473
   2.750   0.7139   0.00900   0.00191  -0.0667   0.3500   0.0500
   3.250   0.7666   0.00907   0.00194  -0.0659   0.3324   0.0577
   3.500   0.7926   0.00912   0.00198  -0.0655   0.3239   0.0669
   3.750   0.8188   0.00910   0.00206  -0.0651   0.3160   0.1210
   4.000   0.8786   0.00764   0.00239  -0.0729   0.3010   1.0000
   4.250   0.9025   0.00780   0.00248  -0.0720   0.2917   1.0000
   4.500   0.9265   0.00796   0.00259  -0.0712   0.2814   1.0000
   4.750   0.9505   0.00813   0.00271  -0.0704   0.2707   1.0000
   5.000   0.9743   0.00832   0.00284  -0.0695   0.2598   1.0000
   5.250   0.9978   0.00853   0.00299  -0.0686   0.2477   1.0000
   5.500   1.0211   0.00877   0.00315  -0.0678   0.2345   1.0000
   5.750   1.0446   0.00900   0.00332  -0.0669   0.2220   1.0000
   6.000   1.0677   0.00926   0.00351  -0.0660   0.2088   1.0000
   6.250   1.0907   0.00953   0.00372  -0.0651   0.1959   1.0000
   6.500   1.1135   0.00983   0.00396  -0.0642   0.1826   1.0000
   6.750   1.1362   0.01015   0.00420  -0.0633   0.1696   1.0000
   7.000   1.1588   0.01047   0.00445  -0.0624   0.1571   1.0000
   7.250   1.1812   0.01082   0.00473  -0.0614   0.1431   1.0000
   7.500   1.2016   0.01134   0.00510  -0.0602   0.1181   1.0000
   7.750   1.2145   0.01252   0.00595  -0.0579   0.0631   1.0000
   8.000   1.2362   0.01292   0.00634  -0.0569   0.0591   1.0000
   8.250   1.2580   0.01331   0.00673  -0.0559   0.0554   1.0000
   8.500   1.2805   0.01361   0.00707  -0.0550   0.0537   1.0000
   8.750   1.3031   0.01390   0.00740  -0.0542   0.0524   1.0000
   9.000   1.3250   0.01424   0.00778  -0.0533   0.0506   1.0000
   9.250   1.3460   0.01465   0.00820  -0.0522   0.0484   1.0000
   9.500   1.3659   0.01512   0.00869  -0.0510   0.0453   1.0000
   9.750   1.3876   0.01542   0.00903  -0.0501   0.0436   1.0000
  10.000   1.4098   0.01568   0.00931  -0.0493   0.0410   1.0000
  10.250   1.4290   0.01614   0.00974  -0.0481   0.0357   1.0000
  10.500   1.4455   0.01677   0.01023  -0.0465   0.0223   1.0000
  10.750   1.4603   0.01747   0.01092  -0.0446   0.0177   1.0000
  11.000   1.4743   0.01819   0.01165  -0.0425   0.0158   1.0000
  11.250   1.4878   0.01878   0.01230  -0.0403   0.0149   1.0000
  11.500   1.4988   0.01939   0.01297  -0.0377   0.0142   1.0000
  11.750   1.5083   0.02009   0.01374  -0.0350   0.0137   1.0000
  12.000   1.5155   0.02093   0.01464  -0.0321   0.0130   1.0000
  12.250   1.5191   0.02201   0.01580  -0.0290   0.0124   1.0000
  12.500   1.5244   0.02305   0.01692  -0.0263   0.0120   1.0000
  12.750   1.5329   0.02395   0.01790  -0.0243   0.0117   1.0000
  13.000   1.5389   0.02508   0.01911  -0.0222   0.0114   1.0000
  13.250   1.5426   0.02646   0.02057  -0.0202   0.0110   1.0000
  13.500   1.5462   0.02796   0.02215  -0.0185   0.0108   1.0000
  13.750   1.5474   0.02979   0.02407  -0.0170   0.0106   1.0000
  14.000   1.5470   0.03193   0.02630  -0.0159   0.0104   1.0000
  14.250   1.5430   0.03459   0.02906  -0.0150   0.0101   1.0000
  14.500   1.5378   0.03762   0.03220  -0.0146   0.0099   1.0000
  14.750   1.5245   0.04185   0.03656  -0.0147   0.0097   1.0000
  15.000   1.5181   0.04557   0.04039  -0.0153   0.0097   1.0000
  15.250   1.4969   0.05150   0.04648  -0.0168   0.0095   1.0000
  15.500   1.4834   0.05664   0.05175  -0.0183   0.0095   1.0000
  15.750   1.4725   0.06151   0.05674  -0.0198   0.0094   1.0000
  16.000   1.4607   0.06659   0.06192  -0.0214   0.0094   1.0000
  16.250   1.4503   0.07156   0.06700  -0.0230   0.0093   1.0000
  16.500   1.4382   0.07681   0.07235  -0.0247   0.0093   1.0000
  16.750   1.4271   0.08202   0.07767  -0.0266   0.0092   1.0000
  17.000   1.4133   0.08775   0.08350  -0.0287   0.0092   1.0000
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