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EPPLER 638 AIRFOIL (e638-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 638 AIRFOIL (e638-il)
Reynolds number: 50,000
Max Cl/Cd: 14.37 at α=0°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e638-il-50000.txt
Download as CSV file: xf-e638-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 638 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3147   0.10511   0.09921  -0.0194   1.0000   0.1916
  -8.500  -0.3013   0.10093   0.09511  -0.0186   1.0000   0.1998
  -8.250  -0.3192   0.09984   0.09420  -0.0206   1.0000   0.2082
  -8.000  -0.3034   0.09575   0.09019  -0.0192   1.0000   0.2218
  -7.750  -0.2973   0.09252   0.08708  -0.0185   1.0000   0.2349
  -7.500  -0.2967   0.08976   0.08447  -0.0178   1.0000   0.2483
  -7.250  -0.2982   0.08722   0.08209  -0.0167   1.0000   0.2644
  -7.000  -0.3268   0.08658   0.08175  -0.0157   1.0000   0.2706
  -6.750  -0.3609   0.08678   0.08229  -0.0125   1.0000   0.2714
  -6.500  -0.3910   0.08750   0.08322  -0.0059   1.0000   0.2697
  -6.250  -0.3986   0.08593   0.08173  -0.0081   0.9893   0.2869
  -5.250   0.0235   0.05810   0.05360  -0.0157   0.9643   0.9028
  -4.750   0.0132   0.05457   0.05000  -0.0245   0.9157   0.7658
  -4.500  -0.0628   0.05423   0.04974  -0.0263   0.8870   0.6368
  -4.250  -0.1152   0.05263   0.04820  -0.0279   0.8632   0.5746
  -4.000  -0.1335   0.04713   0.04149  -0.0549   0.8405   0.3297
  -3.750  -0.0855   0.04366   0.03632  -0.0609   0.8267   0.1910
  -3.500  -0.0553   0.04159   0.03347  -0.0603   0.8136   0.1603
  -3.250  -0.0265   0.03988   0.03108  -0.0592   0.8013   0.1454
  -3.000   0.0044   0.03776   0.02864  -0.0589   0.7906   0.1433
  -2.750   0.0273   0.03661   0.02718  -0.0577   0.7778   0.1421
  -2.500   0.0527   0.03554   0.02580  -0.0568   0.7658   0.1399
  -2.250   0.0832   0.03449   0.02442  -0.0563   0.7554   0.1400
  -2.000   0.1156   0.03375   0.02329  -0.0560   0.7455   0.1457
  -1.750   0.1505   0.03287   0.02241  -0.0569   0.7341   0.1530
  -1.500   0.3459   0.02633   0.01836  -0.0812   0.7209   1.0000
  -1.250   0.3674   0.02678   0.01823  -0.0795   0.7126   1.0000
  -1.000   0.3827   0.02770   0.01889  -0.0784   0.7021   1.0000
  -0.750   0.4003   0.02845   0.01936  -0.0770   0.6936   1.0000
  -0.500   0.4171   0.02927   0.01995  -0.0757   0.6851   1.0000
  -0.250   0.4320   0.03031   0.02081  -0.0745   0.6772   1.0000
   0.000   0.4484   0.03120   0.02152  -0.0731   0.6694   1.0000
   0.250   0.4612   0.03240   0.02258  -0.0717   0.6620   1.0000
   0.500   0.4743   0.03359   0.02363  -0.0702   0.6548   1.0000
   0.750   0.4903   0.03464   0.02453  -0.0688   0.6488   1.0000
   1.000   0.4923   0.03657   0.02643  -0.0670   0.6414   1.0000
   1.250   0.5146   0.03725   0.02693  -0.0658   0.6359   1.0000
   1.500   0.5049   0.03995   0.02962  -0.0633   0.6296   1.0000
   1.750   0.5082   0.04182   0.03142  -0.0614   0.6242   1.0000
   2.000   0.5360   0.04241   0.03185  -0.0607   0.6193   1.0000
   2.250   0.5024   0.04630   0.03576  -0.0568   0.6148   1.0000
   2.500   0.4848   0.04924   0.03865  -0.0537   0.6123   1.0000
   2.750   0.4667   0.05193   0.04128  -0.0501   0.6108   1.0000
   3.000   0.4567   0.05433   0.04362  -0.0474   0.6096   1.0000
   3.250   0.4428   0.05705   0.04628  -0.0450   0.6116   1.0000
   3.500   0.4389   0.05967   0.04884  -0.0438   0.6154   1.0000
   3.750   0.4426   0.06224   0.05136  -0.0434   0.6209   1.0000
   4.000   0.2936   0.06818   0.05763  -0.0388   0.7814   1.0000
   4.250   0.3123   0.07028   0.05961  -0.0390   0.7713   1.0000
   4.500   0.3434   0.07316   0.06238  -0.0408   0.7598   1.0000
   4.750   0.3525   0.07434   0.06350  -0.0396   0.7459   1.0000
   5.000   0.3614   0.07579   0.06488  -0.0385   0.7331   1.0000
   5.250   0.3741   0.07769   0.06671  -0.0380   0.7222   1.0000
   5.500   0.4081   0.08110   0.07006  -0.0402   0.7131   1.0000
   5.750   0.4132   0.08215   0.07107  -0.0386   0.6994   1.0000
   6.000   0.4189   0.08362   0.07251  -0.0374   0.6877   1.0000
   6.250   0.4393   0.08639   0.07525  -0.0380   0.6799   1.0000
   6.750   0.4608   0.08992   0.07873  -0.0368   0.6554   1.0000
   7.000   0.4729   0.09222   0.08102  -0.0365   0.6464   1.0000
   7.500   0.4981   0.09642   0.08523  -0.0360   0.6243   1.0000
   7.750   0.5095   0.09884   0.08764  -0.0359   0.6153   1.0000
   8.000   0.5321   0.10173   0.09055  -0.0365   0.6055   1.0000
   8.250   0.5315   0.10316   0.09199  -0.0353   0.5941   1.0000
   8.500   0.5483   0.10620   0.09507  -0.0357   0.5862   1.0000
   8.750   0.5630   0.10855   0.09746  -0.0357   0.5749   1.0000
   9.000   0.5621   0.11026   0.09919  -0.0349   0.5649   1.0000
   9.250   0.5988   0.11509   0.10407  -0.0366   0.5575   1.0000
   9.500   0.5890   0.11552   0.10453  -0.0351   0.5453   1.0000
   9.750   0.5922   0.11784   0.10688  -0.0348   0.5364   1.0000
  10.000   0.6203   0.12181   0.11095  -0.0357   0.5275   1.0000
  10.250   0.6127   0.12292   0.11208  -0.0348   0.5165   1.0000
  10.500   0.6280   0.12642   0.11564  -0.0353   0.5095   1.0000
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