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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 50,000
Max Cl/Cd: 29.33 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e297-il-50000.txt
Download as CSV file: xf-e297-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 297 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6440   0.09890   0.09252  -0.0195   1.0000   0.1320
 -10.250  -0.6486   0.09137   0.08502  -0.0233   1.0000   0.1217
 -10.000  -0.7065   0.08089   0.07453  -0.0324   1.0000   0.1056
  -9.750  -0.7288   0.07628   0.06982  -0.0331   1.0000   0.1021
  -9.500  -0.7401   0.07175   0.06524  -0.0325   1.0000   0.1000
  -9.250  -0.7547   0.06737   0.06071  -0.0316   1.0000   0.0976
  -9.000  -0.7735   0.06279   0.05583  -0.0301   1.0000   0.0946
  -8.750  -0.7986   0.05912   0.05134  -0.0268   1.0000   0.0905
  -8.500  -0.7943   0.05468   0.04661  -0.0251   1.0000   0.0900
  -8.250  -0.7928   0.05112   0.04254  -0.0226   1.0000   0.0906
  -8.000  -0.7770   0.04763   0.03925  -0.0218   1.0000   0.0986
  -7.750  -0.7709   0.04429   0.03537  -0.0192   1.0000   0.1014
  -7.500  -0.7612   0.04102   0.03144  -0.0163   1.0000   0.1035
  -7.250  -0.7428   0.03778   0.02822  -0.0149   1.0000   0.1122
  -7.000  -0.7285   0.03539   0.02565  -0.0128   1.0000   0.1251
  -6.750  -0.7068   0.03258   0.02255  -0.0111   1.0000   0.1378
  -6.500  -0.6869   0.03031   0.02028  -0.0093   1.0000   0.1610
  -6.250  -0.6669   0.02814   0.01827  -0.0074   1.0000   0.1969
  -6.000  -0.6545   0.02614   0.01673  -0.0045   1.0000   0.2519
  -5.750  -0.6494   0.02403   0.01538  -0.0005   1.0000   0.3340
  -5.500  -0.6524   0.02224   0.01470   0.0055   1.0000   0.4528
  -5.250  -0.6468   0.02240   0.01574   0.0132   1.0000   0.5949
  -5.000  -0.6293   0.02458   0.01791   0.0206   1.0000   0.6781
  -4.750  -0.6004   0.02715   0.02016   0.0264   1.0000   0.7330
  -4.500  -0.5297   0.03030   0.02262   0.0264   1.0000   0.7830
  -4.250  -0.4295   0.03198   0.02354   0.0188   1.0000   0.8303
  -4.000  -0.3249   0.03193   0.02277   0.0075   1.0000   0.8692
  -3.750  -0.2689   0.03120   0.02169   0.0023   1.0000   0.9000
  -3.500  -0.2067   0.03010   0.02026  -0.0047   1.0000   0.9278
  -3.250  -0.1466   0.02879   0.01865  -0.0120   1.0000   0.9531
  -3.000  -0.0834   0.02719   0.01683  -0.0204   1.0000   0.9760
  -2.750  -0.0196   0.02548   0.01490  -0.0294   1.0000   0.9973
  -2.500  -0.0053   0.02498   0.01435  -0.0293   1.0000   1.0000
  -2.250  -0.0020   0.02478   0.01414  -0.0270   1.0000   1.0000
  -2.000  -0.0007   0.02467   0.01401  -0.0244   1.0000   1.0000
  -1.750  -0.0008   0.02460   0.01393  -0.0214   1.0000   1.0000
  -1.500  -0.0012   0.02456   0.01388  -0.0183   1.0000   1.0000
  -1.250  -0.0016   0.02453   0.01383  -0.0152   1.0000   1.0000
  -1.000  -0.0017   0.02450   0.01378  -0.0122   1.0000   1.0000
  -0.750  -0.0016   0.02448   0.01374  -0.0091   1.0000   1.0000
  -0.500  -0.0012   0.02446   0.01371  -0.0061   1.0000   1.0000
  -0.250  -0.0006   0.02445   0.01369  -0.0030   1.0000   1.0000
   0.000   0.0000   0.02444   0.01369   0.0000   1.0000   1.0000
   0.250   0.0006   0.02445   0.01369   0.0030   1.0000   1.0000
   0.500   0.0012   0.02446   0.01371   0.0061   1.0000   1.0000
   0.750   0.0016   0.02447   0.01373   0.0091   1.0000   1.0000
   1.000   0.0017   0.02449   0.01377   0.0122   1.0000   1.0000
   1.250   0.0016   0.02452   0.01382   0.0153   1.0000   1.0000
   1.500   0.0012   0.02455   0.01386   0.0184   1.0000   1.0000
   1.750   0.0007   0.02459   0.01392   0.0214   1.0000   1.0000
   2.000   0.0007   0.02465   0.01400   0.0244   1.0000   1.0000
   2.250   0.0020   0.02476   0.01412   0.0270   1.0000   1.0000
   2.500   0.0054   0.02496   0.01433   0.0293   1.0000   1.0000
   2.750   0.0200   0.02547   0.01488   0.0293   0.9973   1.0000
   3.000   0.0834   0.02717   0.01680   0.0204   0.9761   1.0000
   3.250   0.1466   0.02877   0.01863   0.0120   0.9533   1.0000
   3.500   0.2064   0.03006   0.02023   0.0047   0.9279   1.0000
   3.750   0.2692   0.03117   0.02166  -0.0024   0.9000   1.0000
   4.000   0.3252   0.03190   0.02274  -0.0076   0.8692   1.0000
   4.250   0.4303   0.03194   0.02351  -0.0189   0.8304   1.0000
   4.500   0.5298   0.03027   0.02259  -0.0264   0.7830   1.0000
   4.750   0.6004   0.02713   0.02014  -0.0264   0.7334   1.0000
   5.000   0.6289   0.02457   0.01789  -0.0205   0.6784   1.0000
   5.250   0.6463   0.02239   0.01573  -0.0131   0.5957   1.0000
   5.500   0.6518   0.02222   0.01469  -0.0054   0.4542   1.0000
   5.750   0.6490   0.02400   0.01534   0.0005   0.3352   1.0000
   6.000   0.6540   0.02612   0.01669   0.0046   0.2527   1.0000
   6.250   0.6663   0.02812   0.01824   0.0075   0.1973   1.0000
   6.500   0.6866   0.03030   0.02028   0.0094   0.1617   1.0000
   6.750   0.7062   0.03255   0.02252   0.0112   0.1381   1.0000
   7.000   0.7280   0.03537   0.02563   0.0129   0.1253   1.0000
   7.250   0.7426   0.03776   0.02819   0.0150   0.1124   1.0000
   7.500   0.7611   0.04100   0.03142   0.0163   0.1036   1.0000
   7.750   0.7709   0.04430   0.03538   0.0192   0.1014   1.0000
   8.000   0.7772   0.04766   0.03927   0.0218   0.0986   1.0000
   8.250   0.7930   0.05116   0.04258   0.0226   0.0906   1.0000
   8.500   0.7942   0.05475   0.04670   0.0251   0.0899   1.0000
   8.750   0.7996   0.05921   0.05142   0.0267   0.0905   1.0000
   9.000   0.7736   0.06293   0.05597   0.0300   0.0946   1.0000
   9.250   0.7548   0.06753   0.06088   0.0315   0.0975   1.0000
   9.500   0.7408   0.07190   0.06539   0.0322   0.1001   1.0000
   9.750   0.7312   0.07643   0.06997   0.0329   0.1023   1.0000
  10.000   0.6087   0.07604   0.07007   0.0328   0.1151   1.0000
  10.250   0.6006   0.08192   0.07594   0.0314   0.1166   1.0000
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