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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.14 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e639-il-1000000-n5.txt
Download as CSV file: xf-e639-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 639 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2062   0.08420   0.08094  -0.0546   0.5708   0.0064
  -9.000  -0.2065   0.08056   0.07729  -0.0561   0.5629   0.0066
  -8.750  -0.2116   0.07607   0.07280  -0.0581   0.5571   0.0070
  -8.500  -0.2216   0.07119   0.06796  -0.0606   0.5535   0.0071
  -8.000  -0.2497   0.06255   0.05932  -0.0644   0.5428   0.0074
  -7.750  -0.2472   0.05950   0.05622  -0.0655   0.5359   0.0075
  -7.500  -0.2395   0.05714   0.05380  -0.0661   0.5291   0.0076
  -7.250  -0.2354   0.05348   0.05006  -0.0667   0.5235   0.0077
  -7.000  -0.2282   0.05007   0.04655  -0.0670   0.5174   0.0078
  -6.750  -0.2173   0.04726   0.04364  -0.0669   0.5116   0.0080
  -6.500  -0.2055   0.04431   0.04056  -0.0666   0.5051   0.0083
  -6.000  -0.1835   0.03664   0.03251  -0.0647   0.4939   0.0087
  -5.750  -0.1726   0.03216   0.02776  -0.0628   0.4887   0.0089
  -5.500  -0.1864   0.01837   0.01271  -0.0555   0.4887   0.0101
  -5.250  -0.1640   0.01726   0.01139  -0.0546   0.4818   0.0102
  -5.000  -0.1396   0.01665   0.01065  -0.0540   0.4746   0.0104
  -4.750  -0.1152   0.01597   0.00983  -0.0533   0.4684   0.0105
  -4.500  -0.0901   0.01531   0.00903  -0.0528   0.4629   0.0107
  -4.250  -0.0650   0.01463   0.00820  -0.0522   0.4569   0.0109
  -4.000  -0.0397   0.01394   0.00736  -0.0516   0.4515   0.0111
  -3.750  -0.0139   0.01336   0.00667  -0.0511   0.4457   0.0113
  -3.500   0.0119   0.01280   0.00597  -0.0505   0.4399   0.0115
  -3.250   0.0381   0.01239   0.00547  -0.0501   0.4355   0.0119
  -3.000   0.0644   0.01198   0.00499  -0.0497   0.4308   0.0122
  -2.750   0.0903   0.01157   0.00449  -0.0491   0.4261   0.0124
  -2.500   0.1164   0.01124   0.00409  -0.0487   0.4219   0.0127
  -2.250   0.1427   0.01096   0.00376  -0.0482   0.4175   0.0129
  -2.000   0.1692   0.01080   0.00354  -0.0479   0.4127   0.0131
  -1.500   0.2201   0.01015   0.00282  -0.0467   0.4053   0.0138
  -1.250   0.2464   0.00998   0.00263  -0.0464   0.4016   0.0141
  -1.000   0.2729   0.00985   0.00247  -0.0460   0.3975   0.0145
  -0.750   0.2992   0.00974   0.00233  -0.0456   0.3933   0.0149
  -0.500   0.3260   0.00963   0.00221  -0.0453   0.3901   0.0154
  -0.250   0.3529   0.00955   0.00211  -0.0451   0.3866   0.0161
   0.000   0.3797   0.00948   0.00202  -0.0448   0.3832   0.0166
   0.250   0.4064   0.00944   0.00195  -0.0445   0.3797   0.0170
   0.500   0.4332   0.00936   0.00185  -0.0442   0.3767   0.0179
   0.750   0.4602   0.00932   0.00179  -0.0440   0.3733   0.0190
   1.000   0.4873   0.00930   0.00176  -0.0438   0.3701   0.0202
   1.250   0.5143   0.00930   0.00174  -0.0436   0.3670   0.0218
   1.500   0.5404   0.00923   0.00176  -0.0433   0.3640   0.0606
   1.750   0.5506   0.00768   0.00180  -0.0404   0.3621   0.6653
   2.000   0.5668   0.00704   0.00197  -0.0374   0.3595   0.9294
   2.250   0.6076   0.00719   0.00212  -0.0401   0.3561   0.9608
   2.500   0.6371   0.00731   0.00220  -0.0404   0.3530   0.9713
   2.750   0.6872   0.00753   0.00236  -0.0452   0.3496   0.9806
   3.000   0.7181   0.00762   0.00243  -0.0459   0.3471   0.9840
   3.250   0.7506   0.00770   0.00248  -0.0470   0.3445   0.9848
   3.500   0.7826   0.00778   0.00254  -0.0480   0.3414   0.9857
   3.750   0.8142   0.00787   0.00260  -0.0489   0.3387   0.9868
   4.000   0.8453   0.00798   0.00268  -0.0498   0.3357   0.9881
   4.250   0.8761   0.00807   0.00276  -0.0506   0.3331   0.9894
   4.500   0.9065   0.00815   0.00284  -0.0513   0.3307   0.9909
   4.750   0.9363   0.00825   0.00294  -0.0518   0.3280   0.9924
   5.000   0.9653   0.00836   0.00304  -0.0523   0.3252   0.9938
   5.250   0.9959   0.00847   0.00314  -0.0531   0.3221   0.9948
   5.500   1.0270   0.00859   0.00325  -0.0540   0.3191   0.9957
   5.750   1.0581   0.00867   0.00335  -0.0549   0.3167   0.9968
   6.000   1.0886   0.00878   0.00346  -0.0557   0.3133   0.9978
   6.250   1.1188   0.00891   0.00359  -0.0565   0.3093   0.9989
   6.500   1.1489   0.00906   0.00373  -0.0573   0.3054   0.9998
   6.750   1.1739   0.00917   0.00386  -0.0569   0.3018   1.0000
   7.000   1.1962   0.00930   0.00400  -0.0560   0.2976   1.0000
   7.250   1.2176   0.00948   0.00417  -0.0549   0.2926   1.0000
   7.500   1.2398   0.00961   0.00433  -0.0540   0.2885   1.0000
   7.750   1.2617   0.00977   0.00449  -0.0530   0.2837   1.0000
   8.000   1.2829   0.00996   0.00468  -0.0519   0.2791   1.0000
   8.250   1.3045   0.01012   0.00487  -0.0509   0.2748   1.0000
   8.500   1.3260   0.01029   0.00506  -0.0499   0.2698   1.0000
   8.750   1.3460   0.01054   0.00529  -0.0487   0.2626   1.0000
   9.000   1.3650   0.01085   0.00556  -0.0473   0.2504   1.0000
   9.250   1.3848   0.01111   0.00582  -0.0460   0.2411   1.0000
   9.500   1.4020   0.01150   0.00615  -0.0444   0.2269   1.0000
   9.750   1.4188   0.01191   0.00651  -0.0427   0.2137   1.0000
  10.000   1.4335   0.01242   0.00695  -0.0407   0.1976   1.0000
  10.250   1.4456   0.01303   0.00748  -0.0383   0.1792   1.0000
  10.750   1.4569   0.01475   0.00893  -0.0315   0.1324   1.0000
  11.000   1.4591   0.01548   0.00959  -0.0275   0.1180   1.0000
  11.250   1.4620   0.01625   0.01031  -0.0237   0.1054   1.0000
  11.500   1.4658   0.01707   0.01110  -0.0204   0.0941   1.0000
  11.750   1.4699   0.01797   0.01198  -0.0175   0.0843   1.0000
  12.000   1.4660   0.01938   0.01333  -0.0141   0.0704   1.0000
  12.250   1.4648   0.02087   0.01481  -0.0115   0.0605   1.0000
  12.500   1.4672   0.02237   0.01633  -0.0099   0.0541   1.0000
  12.750   1.4673   0.02425   0.01823  -0.0085   0.0483   1.0000
  13.000   1.4636   0.02669   0.02069  -0.0076   0.0410   1.0000
  13.250   1.4596   0.02941   0.02343  -0.0070   0.0343   1.0000
  13.500   1.4528   0.03257   0.02662  -0.0067   0.0283   1.0000
  13.750   1.4486   0.03559   0.02969  -0.0067   0.0251   1.0000
  14.000   1.4408   0.03904   0.03320  -0.0067   0.0213   1.0000
  14.250   1.4232   0.04362   0.03782  -0.0069   0.0156   1.0000
  14.500   1.4185   0.04684   0.04112  -0.0070   0.0145   1.0000
  14.750   1.4098   0.05054   0.04488  -0.0073   0.0126   1.0000
  15.000   1.3873   0.05594   0.05033  -0.0079   0.0070   1.0000
  15.250   1.3756   0.06025   0.05470  -0.0085   0.0053   1.0000
  15.500   1.3634   0.06469   0.05921  -0.0091   0.0040   1.0000
  15.750   1.3626   0.06775   0.06235  -0.0096   0.0044   1.0000
  16.000   1.3517   0.07216   0.06683  -0.0104   0.0034   1.0000
  16.250   1.3462   0.07589   0.07064  -0.0111   0.0032   1.0000
  16.500   1.3402   0.07978   0.07459  -0.0119   0.0031   1.0000
  16.750   1.3365   0.08340   0.07829  -0.0127   0.0031   1.0000
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