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EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 337 AIRFOIL (e337-il)
Reynolds number: 50,000
Max Cl/Cd: 15.97 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e337-il-50000.txt
Download as CSV file: xf-e337-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 337 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3934   0.11671   0.11036  -0.0108   1.0000   0.2062
  -9.500  -0.3737   0.11211   0.10579  -0.0094   1.0000   0.2182
  -9.250  -0.4017   0.11108   0.10492  -0.0127   1.0000   0.2232
  -9.000  -0.3862   0.10699   0.10087  -0.0114   1.0000   0.2386
  -8.750  -0.3772   0.10341   0.09736  -0.0105   1.0000   0.2541
  -8.500  -0.3715   0.10017   0.09421  -0.0099   1.0000   0.2699
  -8.250  -0.3779   0.09756   0.09172  -0.0096   1.0000   0.2872
  -8.000  -0.3545   0.09342   0.08763  -0.0073   1.0000   0.3095
  -7.750  -0.3551   0.09101   0.08533  -0.0059   1.0000   0.3339
  -7.500  -0.3382   0.08775   0.08215  -0.0037   1.0000   0.3618
  -7.250  -0.3301   0.08522   0.07972  -0.0011   1.0000   0.3967
  -7.000  -0.3106   0.08235   0.07692   0.0025   1.0000   0.4441
  -6.750  -0.2991   0.08040   0.07507   0.0065   1.0000   0.4965
  -6.500  -0.2487   0.07672   0.07141   0.0097   1.0000   0.5735
  -6.250  -0.1954   0.07297   0.06766   0.0113   1.0000   0.6646
  -5.500  -0.2041   0.06556   0.06075   0.0131   1.0000   0.6623
  -5.250  -0.2678   0.06581   0.06145   0.0184   1.0000   0.6271
  -5.000  -0.3073   0.06735   0.06327   0.0258   1.0000   0.6296
  -4.750  -0.3832   0.06161   0.05764   0.0122   0.9626   0.5229
  -4.500  -0.3918   0.05075   0.04456  -0.0200   0.9285   0.2186
  -4.250  -0.3349   0.04566   0.03809  -0.0239   0.9148   0.1375
  -4.000  -0.2857   0.04195   0.03364  -0.0267   0.9011   0.1195
  -3.750  -0.2437   0.03936   0.03028  -0.0279   0.8862   0.1127
  -3.500  -0.2011   0.03700   0.02743  -0.0295   0.8713   0.1125
  -3.250   0.1885   0.02410   0.01691  -0.0772   0.8786   1.0000
  -3.000   0.2173   0.02409   0.01632  -0.0775   0.8546   1.0000
  -2.750   0.2396   0.02427   0.01609  -0.0768   0.8333   1.0000
  -2.500   0.2596   0.02453   0.01602  -0.0757   0.8139   1.0000
  -2.250   0.2793   0.02484   0.01603  -0.0746   0.7965   1.0000
  -2.000   0.2989   0.02518   0.01612  -0.0735   0.7810   1.0000
  -1.750   0.3190   0.02556   0.01625  -0.0725   0.7669   1.0000
  -1.500   0.3398   0.02593   0.01639  -0.0715   0.7541   1.0000
  -1.250   0.3597   0.02638   0.01665  -0.0705   0.7413   1.0000
  -1.000   0.3790   0.02696   0.01708  -0.0697   0.7290   1.0000
  -0.750   0.3984   0.02752   0.01749  -0.0687   0.7184   1.0000
  -0.500   0.4183   0.02799   0.01779  -0.0675   0.7084   1.0000
  -0.250   0.4365   0.02880   0.01852  -0.0669   0.6976   1.0000
   0.000   0.4565   0.02936   0.01893  -0.0657   0.6894   1.0000
   0.250   0.4740   0.03025   0.01977  -0.0650   0.6794   1.0000
   0.500   0.4924   0.03105   0.02048  -0.0640   0.6712   1.0000
   0.750   0.5096   0.03198   0.02136  -0.0631   0.6626   1.0000
   1.000   0.5265   0.03296   0.02229  -0.0621   0.6549   1.0000
   1.250   0.5418   0.03409   0.02339  -0.0611   0.6468   1.0000
   1.500   0.5587   0.03508   0.02432  -0.0599   0.6400   1.0000
   1.750   0.5682   0.03675   0.02602  -0.0589   0.6321   1.0000
   2.000   0.5895   0.03736   0.02654  -0.0576   0.6264   1.0000
   2.250   0.5879   0.03991   0.02918  -0.0561   0.6184   1.0000
   2.500   0.6026   0.04109   0.03033  -0.0547   0.6124   1.0000
   2.750   0.6043   0.04327   0.03253  -0.0529   0.6063   1.0000
   3.000   0.5970   0.04592   0.03522  -0.0505   0.6000   1.0000
   3.250   0.6187   0.04672   0.03597  -0.0493   0.5947   1.0000
   3.500   0.5927   0.05048   0.03977  -0.0458   0.5903   1.0000
   3.750   0.5599   0.05416   0.04344  -0.0414   0.5872   1.0000
   4.000   0.5260   0.05724   0.04649  -0.0361   0.5858   1.0000
   4.250   0.4980   0.06008   0.04930  -0.0315   0.5866   1.0000
   4.500   0.4803   0.06269   0.05188  -0.0282   0.5880   1.0000
   4.750   0.4710   0.06518   0.05435  -0.0259   0.5901   1.0000
   5.000   0.4741   0.06773   0.05690  -0.0250   0.5944   1.0000
   5.250   0.3199   0.07423   0.06346  -0.0187   0.7414   1.0000
   5.500   0.3274   0.07560   0.06480  -0.0172   0.7272   1.0000
   5.750   0.3348   0.07717   0.06633  -0.0158   0.7149   1.0000
   6.000   0.3548   0.07973   0.06888  -0.0162   0.7053   1.0000
   6.250   0.3758   0.08206   0.07120  -0.0163   0.6916   1.0000
   6.500   0.3768   0.08307   0.07218  -0.0141   0.6777   1.0000
   6.750   0.3801   0.08458   0.07368  -0.0125   0.6660   1.0000
   7.000   0.4039   0.08766   0.07677  -0.0133   0.6574   1.0000
   7.250   0.4153   0.08941   0.07853  -0.0124   0.6436   1.0000
   7.500   0.4144   0.09059   0.07971  -0.0104   0.6307   1.0000
   7.750   0.4223   0.09272   0.08184  -0.0096   0.6212   1.0000
   8.000   0.4525   0.09623   0.08539  -0.0108   0.6102   1.0000
   8.250   0.4468   0.09700   0.08615  -0.0086   0.5971   1.0000
   8.500   0.4496   0.09889   0.08805  -0.0076   0.5870   1.0000
   8.750   0.4832   0.10305   0.09230  -0.0091   0.5778   1.0000
   9.000   0.4744   0.10361   0.09286  -0.0070   0.5648   1.0000
   9.250   0.4766   0.10561   0.09488  -0.0061   0.5548   1.0000
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