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EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 398 AIRFOIL (e398-il)
Reynolds number: 50,000
Max Cl/Cd: 6.57 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e398-il-50000.txt
Download as CSV file: xf-e398-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 398 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4100   0.12492   0.11969  -0.0157   1.0000   0.2474
  -7.500  -0.3876   0.11996   0.11470  -0.0135   1.0000   0.2574
  -7.250  -0.4142   0.12010   0.11496  -0.0118   1.0000   0.2624
  -7.000  -0.4118   0.11676   0.11165  -0.0101   1.0000   0.2681
  -6.750  -0.4210   0.11533   0.11028  -0.0080   1.0000   0.2762
  -6.500  -0.4550   0.11569   0.11077  -0.0057   1.0000   0.2791
  -6.250  -0.4383   0.11152   0.10657  -0.0039   1.0000   0.2903
  -6.000  -0.4700   0.11141   0.10658  -0.0011   1.0000   0.2945
  -5.750  -0.4639   0.10797   0.10315   0.0008   1.0000   0.3031
  -5.500  -0.5268   0.08722   0.08233  -0.0337   1.0000   0.1690
  -5.250  -0.5221   0.08510   0.08027  -0.0298   1.0000   0.1713
  -5.000  -0.5114   0.07735   0.07237  -0.0366   1.0000   0.1628
  -4.750  -0.4643   0.05796   0.05188  -0.0631   1.0000   0.1555
  -4.500  -0.4428   0.05535   0.04907  -0.0649   1.0000   0.1650
  -4.250  -0.4154   0.05190   0.04526  -0.0686   1.0000   0.1761
  -4.000  -0.3840   0.04858   0.04144  -0.0727   1.0000   0.1894
  -3.750  -0.3556   0.04647   0.03896  -0.0753   1.0000   0.2045
  -3.500  -0.3301   0.04519   0.03743  -0.0766   1.0000   0.2208
  -3.250  -0.3064   0.04437   0.03645  -0.0774   1.0000   0.2389
  -3.000  -0.2817   0.04366   0.03552  -0.0784   1.0000   0.2590
  -2.750  -0.2562   0.04305   0.03467  -0.0795   1.0000   0.2817
  -2.500  -0.2359   0.04297   0.03461  -0.0792   1.0000   0.3028
  -2.250  -0.2116   0.04280   0.03424  -0.0799   1.0000   0.3296
  -2.000  -0.1926   0.04292   0.03441  -0.0793   1.0000   0.3525
  -1.750  -0.1704   0.04300   0.03439  -0.0796   1.0000   0.3803
  -1.500  -0.1508   0.04327   0.03467  -0.0791   1.0000   0.4069
  -1.250  -0.1308   0.04356   0.03495  -0.0788   1.0000   0.4345
  -1.000  -0.1101   0.04392   0.03527  -0.0787   1.0000   0.4645
  -0.750  -0.0898   0.04436   0.03568  -0.0785   1.0000   0.4954
  -0.500  -0.0702   0.04486   0.03617  -0.0781   1.0000   0.5266
  -0.250  -0.0516   0.04541   0.03675  -0.0775   1.0000   0.5581
   0.000  -0.0326   0.04602   0.03735  -0.0770   1.0000   0.5915
   0.250  -0.0141   0.04666   0.03800  -0.0764   1.0000   0.6268
   0.500   0.0027   0.04730   0.03868  -0.0753   1.0000   0.6635
   0.750   0.0200   0.04796   0.03937  -0.0744   1.0000   0.7063
   1.000   0.0346   0.04851   0.04003  -0.0728   1.0000   0.7550
   1.250   0.0451   0.04879   0.04051  -0.0700   1.0000   0.8192
   1.500   0.0421   0.04759   0.03966  -0.0658   1.0000   0.9599
   1.750   0.0995   0.05019   0.04168  -0.0766   0.9947   1.0000
   2.000   0.1364   0.05231   0.04343  -0.0814   0.9878   1.0000
   2.250   0.1728   0.05487   0.04567  -0.0856   0.9818   1.0000
   2.500   0.2056   0.05701   0.04757  -0.0889   0.9722   1.0000
   2.750   0.2311   0.05868   0.04908  -0.0909   0.9622   1.0000
   3.000   0.2579   0.06069   0.05094  -0.0931   0.9535   1.0000
   3.250   0.2944   0.06359   0.05365  -0.0967   0.9443   1.0000
   3.500   0.3144   0.06488   0.05486  -0.0976   0.9323   1.0000
   3.750   0.3353   0.06658   0.05648  -0.0986   0.9215   1.0000
   4.000   0.3690   0.06959   0.05937  -0.1017   0.9134   1.0000
   4.250   0.3904   0.07114   0.06087  -0.1027   0.9004   1.0000
   4.500   0.4073   0.07267   0.06238  -0.1031   0.8884   1.0000
   4.750   0.4306   0.07499   0.06465  -0.1045   0.8793   1.0000
   5.000   0.4624   0.07775   0.06736  -0.1070   0.8678   1.0000
   5.250   0.4756   0.07908   0.06870  -0.1068   0.8547   1.0000
   5.500   0.4918   0.08101   0.07062  -0.1072   0.8436   1.0000
   5.750   0.5240   0.08426   0.07386  -0.1098   0.8344   1.0000
   6.000   0.5417   0.08600   0.07562  -0.1102   0.8210   1.0000
   6.250   0.5536   0.08768   0.07732  -0.1100   0.8081   1.0000
   6.500   0.5696   0.08991   0.07959  -0.1105   0.7970   1.0000
   6.750   0.6039   0.09347   0.08317  -0.1131   0.7871   1.0000
   7.000   0.6175   0.09519   0.08495  -0.1131   0.7731   1.0000
   7.250   0.6270   0.09702   0.08683  -0.1128   0.7599   1.0000
   7.500   0.6401   0.09932   0.08919  -0.1130   0.7477   1.0000
   7.750   0.6619   0.10231   0.09225  -0.1142   0.7374   1.0000
   8.000   0.6954   0.10579   0.09579  -0.1164   0.7241   1.0000
   8.250   0.7002   0.10736   0.09745  -0.1157   0.7101   1.0000
   8.500   0.7084   0.10952   0.09969  -0.1155   0.6965   1.0000
   8.750   0.7189   0.11205   0.10231  -0.1156   0.6840   1.0000
   9.000   0.7344   0.11490   0.10525  -0.1162   0.6719   1.0000
   9.250   0.7576   0.11814   0.10858  -0.1174   0.6594   1.0000
   9.500   0.7808   0.12119   0.11174  -0.1183   0.6449   1.0000
   9.750   0.8001   0.12401   0.11468  -0.1189   0.6295   1.0000
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