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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 500,000
Max Cl/Cd: 88.88 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe613-il-500000-n5.txt
Download as CSV file: xf-goe613-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3511   0.10738   0.10510  -0.0340   1.0000   0.0102
 -10.250  -0.3524   0.10440   0.10215  -0.0340   1.0000   0.0108
 -10.000  -0.3528   0.09945   0.09723  -0.0365   0.9993   0.0114
  -9.750  -0.3530   0.09219   0.08997  -0.0420   0.9971   0.0121
  -9.250  -0.3299   0.08519   0.08297  -0.0490   0.9915   0.0126
  -9.000  -0.3156   0.08220   0.07998  -0.0525   0.9882   0.0131
  -8.750  -0.3040   0.07828   0.07606  -0.0569   0.9844   0.0138
  -8.500  -0.3018   0.07199   0.06979  -0.0638   0.9766   0.0147
  -8.250  -0.3133   0.05750   0.05523  -0.0820   0.9616   0.0159
  -8.000  -0.2939   0.05407   0.05173  -0.0866   0.9549   0.0162
  -7.750  -0.2678   0.04995   0.04749  -0.0927   0.9511   0.0167
  -7.250  -0.2524   0.02930   0.02582  -0.1027   0.9306   0.0210
  -7.000  -0.2236   0.02877   0.02519  -0.1039   0.9250   0.0214
  -6.750  -0.1968   0.02771   0.02401  -0.1047   0.9193   0.0219
  -6.500  -0.1730   0.02663   0.02279  -0.1048   0.9121   0.0225
  -6.250  -0.1499   0.02439   0.02026  -0.1050   0.9056   0.0236
  -6.000  -0.1328   0.02153   0.01700  -0.1037   0.8974   0.0249
  -5.750  -0.1103   0.01944   0.01451  -0.1031   0.8906   0.0260
  -5.500  -0.0884   0.01820   0.01300  -0.1021   0.8823   0.0265
  -5.250  -0.0631   0.01734   0.01192  -0.1017   0.8756   0.0267
  -5.000  -0.0426   0.01559   0.00994  -0.1007   0.8674   0.0277
  -4.750  -0.0172   0.01500   0.00924  -0.1003   0.8596   0.0283
  -4.500   0.0076   0.01436   0.00846  -0.0997   0.8503   0.0287
  -4.250   0.0328   0.01380   0.00779  -0.0992   0.8415   0.0291
  -4.000   0.0583   0.01328   0.00714  -0.0986   0.8306   0.0296
  -3.750   0.0832   0.01276   0.00648  -0.0979   0.8162   0.0300
  -3.500   0.1080   0.01230   0.00589  -0.0972   0.7994   0.0304
  -3.250   0.1329   0.01187   0.00534  -0.0965   0.7838   0.0307
  -3.000   0.1580   0.01150   0.00486  -0.0958   0.7712   0.0312
  -2.500   0.2081   0.01094   0.00411  -0.0945   0.7459   0.0324
  -2.250   0.2329   0.01067   0.00376  -0.0938   0.7333   0.0330
  -2.000   0.2574   0.01042   0.00343  -0.0930   0.7204   0.0334
  -1.750   0.2820   0.01023   0.00316  -0.0922   0.7071   0.0339
  -1.500   0.3064   0.01007   0.00292  -0.0914   0.6926   0.0343
  -1.250   0.3310   0.00996   0.00274  -0.0907   0.6775   0.0347
  -1.000   0.3545   0.00974   0.00245  -0.0897   0.6597   0.0357
  -0.750   0.3780   0.00962   0.00225  -0.0887   0.6391   0.0367
  -0.500   0.4008   0.00960   0.00211  -0.0876   0.6099   0.0377
  -0.250   0.4223   0.00968   0.00203  -0.0863   0.5744   0.0387
   0.000   0.4446   0.00977   0.00198  -0.0851   0.5471   0.0400
   0.250   0.4681   0.00984   0.00195  -0.0841   0.5273   0.0419
   0.500   0.4921   0.00991   0.00194  -0.0834   0.5112   0.0441
   0.750   0.5164   0.00996   0.00192  -0.0826   0.4967   0.0468
   1.000   0.5407   0.01000   0.00191  -0.0819   0.4825   0.0529
   1.250   0.5649   0.01005   0.00193  -0.0811   0.4671   0.0651
   1.500   0.5735   0.00857   0.00209  -0.0779   0.4548   0.6730
   1.750   0.6603   0.00827   0.00239  -0.0907   0.4291   0.9913
   2.000   0.6973   0.00848   0.00248  -0.0929   0.4113   1.0000
   2.250   0.7186   0.00865   0.00255  -0.0916   0.3959   1.0000
   2.500   0.7398   0.00884   0.00264  -0.0903   0.3811   1.0000
   3.250   0.8041   0.00941   0.00297  -0.0864   0.3415   1.0000
   3.500   0.8261   0.00959   0.00310  -0.0852   0.3321   1.0000
   4.000   0.8702   0.00995   0.00338  -0.0829   0.3159   1.0000
   4.250   0.8918   0.01015   0.00354  -0.0817   0.3085   1.0000
   4.500   0.9142   0.01033   0.00370  -0.0807   0.3011   1.0000
   4.750   0.9355   0.01056   0.00388  -0.0794   0.2921   1.0000
   5.000   0.9572   0.01077   0.00406  -0.0783   0.2809   1.0000
   5.250   0.9786   0.01101   0.00425  -0.0771   0.2689   1.0000
   5.500   0.9998   0.01126   0.00445  -0.0759   0.2579   1.0000
   5.750   1.0205   0.01154   0.00466  -0.0746   0.2439   1.0000
   6.000   1.0414   0.01180   0.00488  -0.0734   0.2336   1.0000
   6.250   1.0627   0.01205   0.00511  -0.0722   0.2228   1.0000
   6.500   1.0825   0.01238   0.00537  -0.0709   0.2071   1.0000
   6.750   1.1021   0.01273   0.00565  -0.0694   0.1913   1.0000
   7.000   1.1185   0.01327   0.00601  -0.0675   0.1607   1.0000
   7.250   1.1275   0.01426   0.00667  -0.0645   0.1099   1.0000
   7.750   1.1364   0.01659   0.00848  -0.0566   0.0164   1.0000
   8.000   1.1531   0.01702   0.00895  -0.0548   0.0144   1.0000
   8.250   1.1701   0.01744   0.00944  -0.0530   0.0135   1.0000
   8.500   1.1863   0.01792   0.00998  -0.0512   0.0124   1.0000
   8.750   1.2012   0.01848   0.01061  -0.0492   0.0113   1.0000
   9.000   1.2142   0.01917   0.01139  -0.0469   0.0105   1.0000
   9.250   1.2281   0.01980   0.01209  -0.0449   0.0101   1.0000
   9.500   1.2421   0.02043   0.01280  -0.0430   0.0097   1.0000
   9.750   1.2556   0.02109   0.01352  -0.0411   0.0091   1.0000
  10.000   1.2671   0.02189   0.01440  -0.0389   0.0088   1.0000
  10.250   1.2789   0.02267   0.01525  -0.0370   0.0083   1.0000
  10.500   1.2891   0.02357   0.01621  -0.0349   0.0080   1.0000
  10.750   1.2956   0.02474   0.01746  -0.0326   0.0076   1.0000
  11.000   1.2994   0.02613   0.01894  -0.0300   0.0073   1.0000
  11.250   1.3065   0.02734   0.02024  -0.0281   0.0072   1.0000
  11.500   1.3114   0.02875   0.02175  -0.0260   0.0071   1.0000
  11.750   1.3164   0.03023   0.02333  -0.0242   0.0068   1.0000
  12.000   1.3201   0.03187   0.02507  -0.0225   0.0067   1.0000
  12.250   1.3219   0.03377   0.02708  -0.0209   0.0064   1.0000
  12.500   1.3229   0.03583   0.02924  -0.0195   0.0063   1.0000
  12.750   1.3231   0.03809   0.03160  -0.0184   0.0061   1.0000
  13.000   1.3225   0.04054   0.03415  -0.0175   0.0060   1.0000
  13.250   1.3212   0.04319   0.03690  -0.0168   0.0059   1.0000
  13.500   1.3214   0.04583   0.03963  -0.0165   0.0057   1.0000
  13.750   1.3201   0.04875   0.04264  -0.0164   0.0056   1.0000
  14.000   1.3150   0.05227   0.04627  -0.0165   0.0055   1.0000
  14.250   1.3088   0.05617   0.05027  -0.0170   0.0054   1.0000
  14.500   1.3021   0.06028   0.05449  -0.0179   0.0053   1.0000
  14.750   1.2926   0.06491   0.05923  -0.0188   0.0053   1.0000
  15.000   1.2853   0.06935   0.06378  -0.0200   0.0051   1.0000
  15.250   1.2759   0.07411   0.06864  -0.0212   0.0051   1.0000
  15.500   1.2713   0.07833   0.07299  -0.0224   0.0050   1.0000
  15.750   1.2642   0.08289   0.07766  -0.0237   0.0050   1.0000
  16.000   1.2572   0.08749   0.08235  -0.0251   0.0050   1.0000
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