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EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 552 AIRFOIL (e552-il)
Reynolds number: 50,000
Max Cl/Cd: 10.95 at α=-3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e552-il-50000.txt
Download as CSV file: xf-e552-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 552 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4416   0.09972   0.09310  -0.0574   1.0000   0.1155
 -11.500  -0.4547   0.09290   0.08631  -0.0602   1.0000   0.1129
 -11.250  -0.4731   0.08602   0.07949  -0.0630   1.0000   0.1101
 -11.000  -0.6013   0.07458   0.06784  -0.0719   1.0000   0.1003
 -10.750  -0.6143   0.07078   0.06405  -0.0713   1.0000   0.0996
 -10.500  -0.6365   0.06773   0.06100  -0.0695   1.0000   0.0990
 -10.250  -0.6558   0.06484   0.05810  -0.0673   1.0000   0.0983
 -10.000  -0.6765   0.06220   0.05540  -0.0645   1.0000   0.0979
  -9.750  -0.6961   0.06015   0.05332  -0.0610   1.0000   0.0975
  -9.500  -0.7184   0.05873   0.05186  -0.0566   1.0000   0.0971
  -9.250  -0.7406   0.05752   0.05058  -0.0522   1.0000   0.0968
  -9.000  -0.7576   0.05613   0.04907  -0.0486   1.0000   0.0965
  -8.750  -0.7700   0.05435   0.04709  -0.0456   1.0000   0.0966
  -8.500  -0.7761   0.05243   0.04493  -0.0431   1.0000   0.0968
  -8.250  -0.7789   0.05045   0.04261  -0.0410   1.0000   0.0982
  -8.000  -0.7639   0.04799   0.03964  -0.0417   0.9957   0.1009
  -7.750  -0.7207   0.04502   0.03674  -0.0452   0.9860   0.1095
  -7.500  -0.6788   0.04251   0.03407  -0.0479   0.9760   0.1200
  -7.250  -0.6374   0.04056   0.03219  -0.0498   0.9661   0.1380
  -7.000  -0.5993   0.03863   0.03053  -0.0514   0.9569   0.1672
  -6.750  -0.5790   0.03627   0.02868  -0.0518   0.9460   0.2104
  -6.500  -0.5749   0.03386   0.02802  -0.0501   0.9349   0.3178
  -6.250  -0.5193   0.04673   0.04114  -0.0379   0.9216   0.4942
  -6.000  -0.3590   0.06086   0.05449  -0.0309   0.9171   0.5635
  -5.750  -0.1776   0.06318   0.05596  -0.0409   0.9167   0.6546
  -5.000   0.2795   0.04543   0.03668  -0.0989   0.9137   1.0000
  -4.750   0.3101   0.04413   0.03522  -0.1030   0.9019   1.0000
  -4.500   0.3409   0.04294   0.03388  -0.1068   0.8916   1.0000
  -4.250   0.3709   0.04187   0.03265  -0.1102   0.8818   1.0000
  -4.000   0.3887   0.04152   0.03222  -0.1112   0.8706   1.0000
  -3.750   0.4127   0.04094   0.03153  -0.1131   0.8621   1.0000
  -3.500   0.4280   0.04091   0.03143  -0.1135   0.8526   1.0000
  -3.250   0.4465   0.04077   0.03121  -0.1143   0.8446   1.0000
  -3.000   0.1970   0.05163   0.04246  -0.0697   0.8324   0.8499
  -2.750   0.0924   0.05457   0.04559  -0.0526   0.8220   0.8132
  -2.500   0.0362   0.05550   0.04658  -0.0425   0.8165   0.8003
  -2.250  -0.1202   0.05721   0.04861  -0.0174   0.8137   0.7851
  -2.000  -0.1725   0.05710   0.04859  -0.0080   0.8117   0.7836
  -1.750  -0.2096   0.05660   0.04811  -0.0013   0.8108   0.7840
  -1.500  -0.2354   0.05596   0.04745   0.0034   0.8110   0.7857
  -1.250  -0.2400   0.05560   0.04704   0.0056   0.8114   0.7883
  -1.000  -0.2394   0.05534   0.04670   0.0070   0.8119   0.7913
  -0.750  -0.2369   0.05511   0.04641   0.0080   0.8128   0.7946
  -0.500  -0.2282   0.05503   0.04624   0.0077   0.8147   0.7981
  -0.250  -0.2475   0.05474   0.04594   0.0104   0.8282   0.8007
   0.000  -0.4450   0.04839   0.04016   0.0409   1.0000   0.7996
   0.250  -0.4237   0.04838   0.04002   0.0387   1.0000   0.8032
   0.500  -0.4055   0.04841   0.03995   0.0379   1.0000   0.8071
   0.750  -0.3850   0.04860   0.04002   0.0364   0.9998   0.8115
   1.000  -0.3482   0.04996   0.04122   0.0312   0.9938   0.8159
   1.250  -0.3181   0.05083   0.04199   0.0278   0.9866   0.8202
   1.500  -0.2886   0.05190   0.04295   0.0247   0.9787   0.8251
   1.750  -0.2530   0.05349   0.04442   0.0202   0.9703   0.8305
   2.000  -0.2190   0.05478   0.04562   0.0160   0.9592   0.8352
   2.250  -0.1940   0.05551   0.04629   0.0140   0.9479   0.8404
   2.500  -0.1660   0.05664   0.04735   0.0111   0.9374   0.8467
   2.750  -0.1301   0.05876   0.04940   0.0071   0.9279   0.8532
   3.000  -0.1052   0.05947   0.05007   0.0051   0.9147   0.8597
   3.250  -0.0818   0.06033   0.05090   0.0031   0.9026   0.8663
   3.500  -0.0568   0.06165   0.05220   0.0013   0.8920   0.8741
   3.750  -0.0222   0.06375   0.05428  -0.0022   0.8811   0.8837
   4.000  -0.0041   0.06424   0.05478  -0.0030   0.8678   0.8930
   4.250   0.0172   0.06530   0.05587  -0.0043   0.8558   0.9029
   4.500   0.0509   0.06760   0.05820  -0.0078   0.8467   0.9164
   4.750   0.0803   0.06905   0.05971  -0.0107   0.8330   0.9315
   5.000   0.1065   0.07022   0.06096  -0.0136   0.8194   0.9492
   5.250   0.1380   0.07187   0.06269  -0.0179   0.8057   0.9763
   5.500   0.1656   0.07374   0.06455  -0.0217   0.7940   1.0000
   5.750   0.2116   0.07729   0.06808  -0.0283   0.7833   1.0000
   6.000   0.2301   0.07841   0.06918  -0.0306   0.7694   1.0000
   6.250   0.2524   0.08026   0.07102  -0.0335   0.7565   1.0000
   6.500   0.2806   0.08283   0.07357  -0.0374   0.7457   1.0000
   6.750   0.3249   0.08668   0.07741  -0.0431   0.7346   1.0000
   7.000   0.3394   0.08804   0.07876  -0.0447   0.7205   1.0000
   7.250   0.3556   0.09000   0.08071  -0.0465   0.7080   1.0000
   7.500   0.3789   0.09276   0.08346  -0.0490   0.6974   1.0000
   7.750   0.4171   0.09657   0.08725  -0.0529   0.6860   1.0000
   8.000   0.4239   0.09786   0.08855  -0.0531   0.6724   1.0000
   8.250   0.4352   0.09997   0.09066  -0.0539   0.6601   1.0000
   8.500   0.4579   0.10314   0.09385  -0.0557   0.6505   1.0000
   8.750   0.4855   0.10632   0.09705  -0.0577   0.6380   1.0000
   9.000   0.4893   0.10789   0.09864  -0.0577   0.6247   1.0000
   9.250   0.4985   0.11030   0.10108  -0.0582   0.6137   1.0000
   9.500   0.5299   0.11442   0.10525  -0.0604   0.6042   1.0000
   9.750   0.5397   0.11637   0.10726  -0.0608   0.5907   1.0000
  10.000   0.5416   0.11834   0.10926  -0.0609   0.5787   1.0000
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