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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.12 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe123-il-1000000.txt
Download as CSV file: xf-goe123-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2759   0.08770   0.08611  -0.0362   0.9571   0.0128
  -7.500  -0.2673   0.08524   0.08362  -0.0372   0.9461   0.0129
  -7.250  -0.2554   0.08277   0.08112  -0.0390   0.9370   0.0132
  -7.000  -0.2417   0.08018   0.07851  -0.0416   0.9284   0.0136
  -6.750  -0.2257   0.07724   0.07553  -0.0449   0.9208   0.0143
  -6.500  -0.2018   0.07332   0.07155  -0.0517   0.9125   0.0157
  -6.250  -0.1745   0.06897   0.06714  -0.0598   0.9045   0.0159
  -6.000  -0.1499   0.06504   0.06314  -0.0652   0.8972   0.0159
  -5.750  -0.1300   0.06015   0.05820  -0.0693   0.8902   0.0161
  -5.500  -0.1129   0.05785   0.05586  -0.0701   0.8833   0.0164
  -5.250  -0.0906   0.05560   0.05357  -0.0724   0.8770   0.0168
  -5.000  -0.0646   0.05298   0.05090  -0.0757   0.8707   0.0177
  -4.750  -0.0209   0.04916   0.04691  -0.0834   0.8654   0.0197
  -4.500   0.0123   0.04558   0.04324  -0.0878   0.8598   0.0198
  -4.250   0.0445   0.04203   0.03958  -0.0914   0.8544   0.0199
  -4.000   0.0685   0.03787   0.03531  -0.0942   0.8492   0.0204
  -3.750   0.0940   0.03608   0.03348  -0.0956   0.8429   0.0208
  -3.500   0.1217   0.03422   0.03152  -0.0971   0.8362   0.0215
  -3.250   0.1518   0.03211   0.02932  -0.0990   0.8281   0.0226
  -3.000   0.1905   0.02982   0.02680  -0.1010   0.8205   0.0247
  -2.750   0.2229   0.02725   0.02408  -0.1025   0.8122   0.0248
  -2.500   0.2550   0.02239   0.01891  -0.1049   0.8058   0.0254
  -2.250   0.2823   0.02112   0.01757  -0.1056   0.7987   0.0259
  -2.000   0.3101   0.01999   0.01633  -0.1062   0.7922   0.0264
  -1.750   0.3388   0.01880   0.01504  -0.1067   0.7856   0.0271
   0.000   0.5429   0.01146   0.00658  -0.1081   0.7292   0.0398
   0.250   0.5713   0.00983   0.00472  -0.1084   0.7158   0.0433
   0.500   0.5989   0.00961   0.00443  -0.1084   0.6998   0.0459
   0.750   0.6269   0.00936   0.00407  -0.1083   0.6834   0.0486
   1.000   0.6546   0.00951   0.00412  -0.1080   0.6642   0.0505
   1.250   0.6836   0.00773   0.00200  -0.1076   0.6455   0.0320
   1.500   0.7109   0.00757   0.00174  -0.1075   0.6211   0.0325
   1.750   0.7381   0.00754   0.00160  -0.1074   0.5940   0.0329
   2.000   0.7649   0.00760   0.00154  -0.1072   0.5640   0.0333
   2.250   0.7916   0.00771   0.00153  -0.1071   0.5332   0.0345
   2.500   0.8183   0.00785   0.00155  -0.1069   0.5046   0.0353
   2.750   0.8452   0.00798   0.00159  -0.1067   0.4816   0.0362
   3.000   0.8722   0.00811   0.00164  -0.1066   0.4587   0.0383
   3.250   0.8989   0.00829   0.00171  -0.1064   0.4346   0.0421
   3.500   0.9256   0.00840   0.00188  -0.1063   0.4097   0.1063
   3.750   0.9519   0.00862   0.00206  -0.1062   0.3843   0.1446
   4.000   0.9779   0.00887   0.00224  -0.1060   0.3565   0.1654
   4.250   0.9994   0.00774   0.00257  -0.1052   0.3351   1.0000
   4.500   1.0256   0.00801   0.00274  -0.1050   0.3161   1.0000
   4.750   1.0517   0.00827   0.00291  -0.1048   0.2978   1.0000
   5.000   1.0778   0.00853   0.00310  -0.1045   0.2801   1.0000
   5.250   1.1037   0.00881   0.00329  -0.1043   0.2622   1.0000
   5.500   1.1292   0.00912   0.00350  -0.1040   0.2412   1.0000
   5.750   1.1541   0.00951   0.00376  -0.1037   0.2151   1.0000
   6.000   1.1779   0.01002   0.00408  -0.1032   0.1801   1.0000
   6.250   1.2012   0.01059   0.00446  -0.1026   0.1475   1.0000
   6.500   1.2209   0.01159   0.00509  -0.1016   0.0865   1.0000
   6.750   1.2441   0.01215   0.00557  -0.1010   0.0663   1.0000
   7.000   1.2643   0.01308   0.00626  -0.0999   0.0299   1.0000
   7.250   1.2882   0.01351   0.00671  -0.0994   0.0253   1.0000
   7.500   1.3109   0.01409   0.00729  -0.0986   0.0213   1.0000
   7.750   1.3343   0.01454   0.00779  -0.0980   0.0196   1.0000
   8.000   1.3577   0.01496   0.00825  -0.0974   0.0180   1.0000
   8.250   1.3798   0.01552   0.00881  -0.0966   0.0162   1.0000
   8.500   1.4005   0.01623   0.00959  -0.0956   0.0148   1.0000
   8.750   1.4228   0.01669   0.01009  -0.0949   0.0141   1.0000
   9.000   1.4444   0.01721   0.01066  -0.0940   0.0133   1.0000
   9.250   1.4652   0.01778   0.01126  -0.0931   0.0125   1.0000
   9.500   1.4832   0.01860   0.01213  -0.0918   0.0117   1.0000
   9.750   1.4960   0.01986   0.01351  -0.0896   0.0110   1.0000
  10.000   1.5159   0.02037   0.01407  -0.0886   0.0107   1.0000
  10.250   1.5340   0.02100   0.01476  -0.0873   0.0102   1.0000
  10.500   1.5503   0.02173   0.01555  -0.0857   0.0098   1.0000
  10.750   1.5641   0.02250   0.01639  -0.0838   0.0094   1.0000
  11.000   1.5757   0.02330   0.01724  -0.0815   0.0090   1.0000
  11.250   1.5851   0.02426   0.01826  -0.0791   0.0087   1.0000
  11.500   1.5892   0.02565   0.01974  -0.0761   0.0084   1.0000
  11.750   1.5814   0.02805   0.02230  -0.0720   0.0081   1.0000
  12.000   1.5837   0.02979   0.02415  -0.0694   0.0079   1.0000
  12.250   1.5917   0.03113   0.02558  -0.0677   0.0078   1.0000
  12.500   1.5980   0.03266   0.02721  -0.0659   0.0077   1.0000
  12.750   1.6024   0.03442   0.02908  -0.0641   0.0075   1.0000
  13.000   1.6056   0.03636   0.03113  -0.0624   0.0074   1.0000
  13.250   1.6080   0.03845   0.03332  -0.0609   0.0072   1.0000
  13.500   1.6094   0.04071   0.03569  -0.0595   0.0071   1.0000
  13.750   1.6113   0.04300   0.03809  -0.0584   0.0069   1.0000
  14.000   1.6130   0.04539   0.04058  -0.0575   0.0067   1.0000
  14.250   1.6138   0.04795   0.04324  -0.0568   0.0066   1.0000
  14.500   1.6142   0.05065   0.04603  -0.0563   0.0064   1.0000
  14.750   1.6122   0.05375   0.04923  -0.0560   0.0063   1.0000
  15.000   1.6093   0.05705   0.05262  -0.0559   0.0062   1.0000
  15.250   1.6035   0.06090   0.05659  -0.0561   0.0061   1.0000
  15.500   1.5959   0.06520   0.06101  -0.0565   0.0060   1.0000
  15.750   1.5863   0.06993   0.06586  -0.0573   0.0059   1.0000
  16.000   1.5745   0.07515   0.07122  -0.0584   0.0059   1.0000
  16.250   1.5586   0.08118   0.07739  -0.0599   0.0058   1.0000
  16.500   1.5428   0.08734   0.08371  -0.0616   0.0057   1.0000
  16.750   1.5227   0.09434   0.09088  -0.0637   0.0057   1.0000
  17.000   1.5020   0.10172   0.09843  -0.0663   0.0056   1.0000
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