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EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 553 AIRFOIL (e553-il)
Reynolds number: 50,000
Max Cl/Cd: 4.87 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e553-il-50000.txt
Download as CSV file: xf-e553-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 553 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4368   0.10443   0.09762  -0.0625   1.0000   0.1178
 -11.750  -0.4463   0.09832   0.09155  -0.0641   1.0000   0.1159
 -11.500  -0.5532   0.08215   0.07538  -0.0752   1.0000   0.1027
 -11.250  -0.5741   0.07743   0.07070  -0.0757   1.0000   0.1018
 -11.000  -0.5984   0.07336   0.06663  -0.0755   1.0000   0.1008
 -10.750  -0.6284   0.07006   0.06334  -0.0741   1.0000   0.1000
 -10.500  -0.6599   0.06773   0.06103  -0.0712   1.0000   0.0991
 -10.250  -0.6919   0.06600   0.05930  -0.0673   1.0000   0.0980
 -10.000  -0.7207   0.06390   0.05713  -0.0635   1.0000   0.0972
  -9.750  -0.7452   0.06169   0.05479  -0.0601   1.0000   0.0968
  -9.500  -0.7640   0.05930   0.05222  -0.0569   1.0000   0.0968
  -9.250  -0.7763   0.05680   0.04950  -0.0543   1.0000   0.0969
  -9.000  -0.7829   0.05424   0.04667  -0.0519   1.0000   0.0974
  -8.750  -0.7842   0.05171   0.04384  -0.0498   1.0000   0.0985
  -8.500  -0.7829   0.04936   0.04113  -0.0478   1.0000   0.1009
  -8.250  -0.7776   0.04697   0.03839  -0.0461   1.0000   0.1042
  -8.000  -0.7639   0.04510   0.03664  -0.0444   1.0000   0.1098
  -7.750  -0.7526   0.04329   0.03454  -0.0425   1.0000   0.1159
  -7.500  -0.7384   0.04162   0.03306  -0.0404   1.0000   0.1253
  -7.250  -0.7256   0.04013   0.03163  -0.0381   1.0000   0.1369
  -7.000  -0.7147   0.03874   0.03037  -0.0357   1.0000   0.1517
  -6.750  -0.7067   0.03710   0.02893  -0.0335   1.0000   0.1737
  -6.500  -0.7009   0.03486   0.02712  -0.0319   1.0000   0.2089
  -6.250  -0.6979   0.03277   0.02681  -0.0297   1.0000   0.3163
  -6.000  -0.6882   0.03953   0.03393  -0.0198   1.0000   0.4405
  -5.750  -0.6778   0.04463   0.03898  -0.0110   1.0000   0.4734
  -5.500  -0.6656   0.04958   0.04388  -0.0015   1.0000   0.4957
  -5.250  -0.6565   0.05182   0.04596   0.0042   1.0000   0.5220
  -5.000  -0.6426   0.05527   0.04933   0.0124   1.0000   0.5427
  -4.750  -0.5934   0.05961   0.05339   0.0162   0.9902   0.5775
  -4.500  -0.5438   0.06200   0.05546   0.0172   0.9809   0.6110
  -4.250  -0.5233   0.06173   0.05497   0.0168   0.9719   0.6363
  -4.000  -0.4657   0.06293   0.05588   0.0160   0.9625   0.6635
  -3.750  -0.4390   0.06240   0.05514   0.0148   0.9540   0.6813
  -3.500  -0.4118   0.06174   0.05430   0.0134   0.9452   0.6957
  -3.250  -0.4246   0.06015   0.05264   0.0152   0.9376   0.7015
  -3.000  -0.3857   0.05976   0.05204   0.0125   0.9289   0.7126
  -2.750  -0.3953   0.05833   0.05053   0.0143   0.9216   0.7169
  -2.500  -0.3693   0.05767   0.04972   0.0126   0.9135   0.7237
  -2.250  -0.3636   0.05672   0.04867   0.0132   0.9063   0.7281
  -2.000  -0.3559   0.05568   0.04750   0.0126   0.8995   0.7328
  -1.750  -0.3385   0.05496   0.04664   0.0112   0.8924   0.7371
  -1.500  -0.3260   0.05437   0.04596   0.0114   0.8856   0.7411
  -1.250  -0.2965   0.05407   0.04549   0.0083   0.8783   0.7460
  -1.000  -0.2910   0.05332   0.04465   0.0082   0.8723   0.7494
  -0.750  -0.2668   0.05307   0.04428   0.0062   0.8656   0.7536
  -0.500  -0.2477   0.05295   0.04406   0.0054   0.8593   0.7578
  -0.250  -0.2321   0.05275   0.04378   0.0044   0.8537   0.7616
   0.000  -0.1916   0.05302   0.04388  -0.0007   0.8461   0.7669
   0.250  -0.1864   0.05288   0.04371   0.0005   0.8419   0.7706
   0.500  -0.1703   0.05301   0.04378  -0.0001   0.8374   0.7747
   0.750  -0.1306   0.05360   0.04424  -0.0043   0.8296   0.7801
   1.000  -0.1203   0.05380   0.04439  -0.0048   0.8265   0.7846
   1.250  -0.1087   0.05415   0.04472  -0.0046   0.8243   0.7891
   1.500  -0.0931   0.05471   0.04524  -0.0056   0.8234   0.7941
   1.750  -0.0746   0.05544   0.04592  -0.0076   0.8236   0.7994
   2.000  -0.0604   0.05630   0.04677  -0.0080   0.8272   0.8045
   2.250  -0.1446   0.05615   0.04682   0.0022   0.9425   0.8063
   2.500  -0.1230   0.05653   0.04715   0.0004   0.9318   0.8125
   2.750  -0.0959   0.05787   0.04845  -0.0022   0.9246   0.8188
   3.000  -0.0676   0.05910   0.04966  -0.0048   0.9135   0.8257
   3.250  -0.0466   0.05992   0.05045  -0.0065   0.9040   0.8328
   3.500  -0.0119   0.06220   0.05270  -0.0099   0.8951   0.8416
   3.750   0.0035   0.06244   0.05294  -0.0104   0.8836   0.8493
   4.000   0.0258   0.06383   0.05435  -0.0119   0.8758   0.8582
   4.250   0.0559   0.06552   0.05605  -0.0146   0.8639   0.8686
   4.500   0.0691   0.06608   0.05664  -0.0148   0.8537   0.8790
   4.750   0.1002   0.06834   0.05894  -0.0175   0.8455   0.8930
   5.000   0.1176   0.06899   0.05967  -0.0181   0.8327   0.9071
   5.250   0.1350   0.07008   0.06085  -0.0193   0.8228   0.9240
   5.500   0.1789   0.07298   0.06388  -0.0251   0.8128   0.9520
   5.750   0.2075   0.07438   0.06535  -0.0290   0.7984   1.0000
   6.000   0.2257   0.07569   0.06666  -0.0316   0.7864   1.0000
   6.250   0.2555   0.07821   0.06917  -0.0360   0.7762   1.0000
   6.500   0.3018   0.08187   0.07283  -0.0426   0.7650   1.0000
   6.750   0.3164   0.08317   0.07413  -0.0445   0.7520   1.0000
   7.000   0.3377   0.08544   0.07640  -0.0475   0.7405   1.0000
   7.250   0.3768   0.08918   0.08012  -0.0526   0.7309   1.0000
   7.500   0.4011   0.09147   0.08241  -0.0553   0.7171   1.0000
   7.750   0.4113   0.09320   0.08415  -0.0563   0.7046   1.0000
   8.000   0.4296   0.09580   0.08674  -0.0581   0.6937   1.0000
   8.250   0.4679   0.09982   0.09077  -0.0619   0.6829   1.0000
   8.500   0.4773   0.10144   0.09241  -0.0623   0.6692   1.0000
   8.750   0.4853   0.10348   0.09448  -0.0628   0.6565   1.0000
   9.000   0.5008   0.10631   0.09733  -0.0640   0.6461   1.0000
   9.250   0.5357   0.11031   0.10138  -0.0666   0.6344   1.0000
   9.500   0.5425   0.11208   0.10319  -0.0668   0.6205   1.0000
   9.750   0.5458   0.11420   0.10536  -0.0669   0.6084   1.0000
  10.000   0.5590   0.11713   0.10833  -0.0678   0.5973   1.0000
  10.250   0.5899   0.12117   0.11246  -0.0698   0.5859   1.0000
  10.500   0.6007   0.12346   0.11481  -0.0702   0.5717   1.0000
  10.750   0.6001   0.12551   0.11691  -0.0703   0.5593   1.0000
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