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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 500,000
Max Cl/Cd: 106.84 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe264-il-500000.txt
Download as CSV file: xf-goe264-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3110   0.09615   0.09400  -0.0216   1.0000   0.0198
  -7.750  -0.3059   0.09353   0.09140  -0.0225   1.0000   0.0205
  -7.500  -0.3078   0.09151   0.08943  -0.0220   1.0000   0.0216
  -7.250  -0.2075   0.07213   0.07020  -0.0413   0.9879   0.0227
  -7.000  -0.2878   0.08554   0.08350  -0.0341   0.9954   0.0226
  -6.750  -0.2573   0.08033   0.07827  -0.0428   0.9918   0.0227
  -6.500  -0.2403   0.07460   0.07254  -0.0455   0.9886   0.0232
  -6.250  -0.2150   0.07129   0.06921  -0.0489   0.9860   0.0238
  -6.000  -0.1835   0.06765   0.06553  -0.0551   0.9832   0.0250
  -5.750  -0.1513   0.06370   0.06154  -0.0621   0.9761   0.0273
  -5.500  -0.0925   0.05793   0.05560  -0.0779   0.9701   0.0288
  -5.250  -0.0705   0.05172   0.04933  -0.0827   0.9607   0.0295
  -5.000  -0.0521   0.04978   0.04737  -0.0826   0.9521   0.0302
  -4.750  -0.0298   0.04772   0.04526  -0.0838   0.9423   0.0315
  -4.500   0.0170   0.04500   0.04232  -0.0904   0.9315   0.0366
  -4.250   0.0495   0.04123   0.03838  -0.0938   0.9213   0.0368
  -4.000   0.0725   0.03569   0.03271  -0.0969   0.9109   0.0382
  -3.750   0.0943   0.03453   0.03150  -0.0968   0.8982   0.0395
  -3.500   0.1211   0.03301   0.02988  -0.0976   0.8849   0.0426
  -3.250   0.1635   0.03112   0.02765  -0.1000   0.8714   0.0469
  -3.000   0.1961   0.02520   0.02139  -0.1037   0.8582   0.0487
  -2.750   0.2209   0.02435   0.02046  -0.1038   0.8414   0.0500
  -2.500   0.2484   0.02325   0.01920  -0.1042   0.8241   0.0519
  -2.250   0.2791   0.02177   0.01749  -0.1050   0.8054   0.0558
  -2.000   0.3156   0.01846   0.01363  -0.1069   0.7861   0.0616
  -1.750   0.3531   0.01333   0.00765  -0.1088   0.7665   0.0497
  -1.500   0.3824   0.01232   0.00633  -0.1090   0.7394   0.0498
  -1.250   0.4106   0.01183   0.00560  -0.1090   0.7083   0.0509
  -1.000   0.4387   0.01152   0.00506  -0.1090   0.6788   0.0525
  -0.750   0.4671   0.01111   0.00444  -0.1090   0.6554   0.0537
  -0.500   0.4955   0.01083   0.00398  -0.1090   0.6363   0.0551
  -0.250   0.5238   0.01060   0.00361  -0.1091   0.6198   0.0564
   0.000   0.5522   0.01042   0.00331  -0.1092   0.6049   0.0578
   0.250   0.5806   0.01031   0.00312  -0.1092   0.5910   0.0591
   0.500   0.6094   0.01000   0.00274  -0.1094   0.5773   0.0626
   0.750   0.6379   0.00990   0.00261  -0.1096   0.5631   0.0662
   1.000   0.6663   0.00986   0.00252  -0.1097   0.5490   0.0696
   1.250   0.6947   0.00985   0.00246  -0.1098   0.5350   0.0730
   1.500   0.7233   0.00980   0.00241  -0.1099   0.5208   0.0815
   1.750   0.7515   0.00982   0.00244  -0.1100   0.5062   0.0982
   2.000   0.7797   0.00986   0.00253  -0.1102   0.4913   0.1417
   2.250   0.8077   0.00994   0.00261  -0.1102   0.4762   0.1680
   2.500   0.8356   0.01003   0.00271  -0.1103   0.4616   0.1934
   2.750   0.8637   0.01005   0.00285  -0.1105   0.4480   0.2633
   3.000   0.8840   0.00880   0.00297  -0.1091   0.4365   1.0000
   3.250   0.9116   0.00901   0.00308  -0.1091   0.4252   1.0000
   3.500   0.9393   0.00920   0.00321  -0.1091   0.4149   1.0000
   3.750   0.9669   0.00938   0.00336  -0.1091   0.4057   1.0000
   4.000   0.9942   0.00961   0.00352  -0.1091   0.3971   1.0000
   4.250   1.0219   0.00978   0.00369  -0.1091   0.3886   1.0000
   4.500   1.0491   0.01000   0.00389  -0.1091   0.3809   1.0000
   4.750   1.0764   0.01020   0.00407  -0.1090   0.3717   1.0000
   5.000   1.1035   0.01040   0.00424  -0.1090   0.3585   1.0000
   5.250   1.1303   0.01062   0.00442  -0.1089   0.3447   1.0000
   5.500   1.1571   0.01085   0.00463  -0.1088   0.3311   1.0000
   5.750   1.1838   0.01108   0.00485  -0.1087   0.3182   1.0000
   6.000   1.2103   0.01134   0.00509  -0.1086   0.3046   1.0000
   6.250   1.2363   0.01165   0.00536  -0.1084   0.2853   1.0000
   6.500   1.2611   0.01213   0.00569  -0.1082   0.2513   1.0000
   6.750   1.2721   0.01475   0.00726  -0.1064   0.0727   1.0000
   7.000   1.2906   0.01619   0.00844  -0.1051   0.0293   1.0000
   7.250   1.3129   0.01697   0.00927  -0.1043   0.0240   1.0000
   7.500   1.3355   0.01763   0.00999  -0.1036   0.0213   1.0000
   7.750   1.3544   0.01874   0.01120  -0.1023   0.0190   1.0000
   8.000   1.3737   0.01969   0.01226  -0.1010   0.0181   1.0000
   8.250   1.3928   0.02057   0.01323  -0.0997   0.0172   1.0000
   8.500   1.4109   0.02149   0.01423  -0.0984   0.0162   1.0000
   8.750   1.4278   0.02243   0.01524  -0.0969   0.0151   1.0000
   9.000   1.4400   0.02374   0.01662  -0.0948   0.0143   1.0000
   9.250   1.4418   0.02582   0.01883  -0.0911   0.0137   1.0000
   9.500   1.4456   0.02755   0.02067  -0.0877   0.0134   1.0000
   9.750   1.4530   0.02872   0.02193  -0.0847   0.0131   1.0000
  10.000   1.4588   0.03010   0.02342  -0.0818   0.0129   1.0000
  10.250   1.4641   0.03169   0.02512  -0.0790   0.0126   1.0000
  10.500   1.4694   0.03344   0.02697  -0.0765   0.0123   1.0000
  10.750   1.4751   0.03532   0.02897  -0.0742   0.0120   1.0000
  11.000   1.4814   0.03722   0.03099  -0.0720   0.0117   1.0000
  11.250   1.4877   0.03909   0.03296  -0.0702   0.0113   1.0000
  11.500   1.4936   0.04094   0.03489  -0.0686   0.0110   1.0000
  11.750   1.4981   0.04297   0.03701  -0.0671   0.0106   1.0000
  12.000   1.5021   0.04518   0.03930  -0.0657   0.0103   1.0000
  12.250   1.5060   0.04778   0.04200  -0.0640   0.0101   1.0000
  12.500   1.5098   0.05079   0.04514  -0.0622   0.0099   1.0000
  12.750   1.5116   0.05430   0.04884  -0.0604   0.0098   1.0000
  13.000   1.5096   0.05806   0.05282  -0.0589   0.0098   1.0000
  13.250   1.5039   0.06207   0.05705  -0.0577   0.0098   1.0000
  13.500   1.4959   0.06619   0.06137  -0.0569   0.0098   1.0000
  13.750   1.4860   0.07050   0.06589  -0.0566   0.0098   1.0000
  14.000   1.4756   0.07490   0.07048  -0.0568   0.0098   1.0000
  14.250   1.4631   0.07974   0.07552  -0.0575   0.0098   1.0000
  14.500   1.4516   0.08453   0.08048  -0.0586   0.0099   1.0000
  14.750   1.4373   0.09000   0.08614  -0.0603   0.0099   1.0000
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