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EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 553 AIRFOIL (e553-il)
Reynolds number: 500,000
Max Cl/Cd: 99.29 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e553-il-500000.txt
Download as CSV file: xf-e553-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.5667   0.12927   0.12652  -0.0451   1.0000   0.0094
 -16.750  -0.6028   0.11667   0.11377  -0.0515   1.0000   0.0092
 -16.500  -0.6288   0.10707   0.10403  -0.0565   1.0000   0.0090
 -16.250  -0.6551   0.09797   0.09476  -0.0613   1.0000   0.0089
 -16.000  -0.6730   0.09104   0.08770  -0.0648   1.0000   0.0088
 -15.750  -0.6922   0.08421   0.08070  -0.0682   1.0000   0.0087
 -15.500  -0.7094   0.07809   0.07441  -0.0710   1.0000   0.0086
 -15.250  -0.7243   0.07261   0.06876  -0.0733   1.0000   0.0086
 -15.000  -0.7350   0.06803   0.06402  -0.0750   1.0000   0.0085
 -14.750  -0.7455   0.06365   0.05949  -0.0765   1.0000   0.0086
 -14.500  -0.7510   0.06015   0.05585  -0.0773   1.0000   0.0084
 -14.250  -0.7562   0.05682   0.05239  -0.0781   1.0000   0.0086
 -14.000  -0.7593   0.05389   0.04933  -0.0784   1.0000   0.0086
 -13.750  -0.7621   0.05116   0.04648  -0.0784   1.0000   0.0087
 -13.500  -0.7627   0.04880   0.04402  -0.0781   1.0000   0.0087
 -13.250  -0.7621   0.04668   0.04181  -0.0776   1.0000   0.0087
 -13.000  -0.7613   0.04467   0.03971  -0.0770   1.0000   0.0089
 -12.750  -0.7608   0.04272   0.03767  -0.0762   1.0000   0.0091
 -12.500  -0.7583   0.04113   0.03602  -0.0750   1.0000   0.0090
 -12.250  -0.7580   0.03945   0.03426  -0.0737   1.0000   0.0092
 -12.000  -0.7587   0.03795   0.03270  -0.0720   1.0000   0.0093
 -11.750  -0.7627   0.03665   0.03138  -0.0695   1.0000   0.0093
 -11.500  -0.7492   0.03503   0.02968  -0.0705   0.9985   0.0095
 -11.250  -0.7291   0.03266   0.02730  -0.0737   0.9946   0.0101
 -11.000  -0.7052   0.03077   0.02537  -0.0768   0.9894   0.0102
 -10.750  -0.6802   0.02886   0.02341  -0.0803   0.9835   0.0106
 -10.500  -0.6586   0.02709   0.02159  -0.0828   0.9736   0.0111
 -10.250  -0.6373   0.02531   0.01975  -0.0853   0.9630   0.0115
  -9.750  -0.5838   0.02109   0.01537  -0.0938   0.9454   0.0128
  -9.500  -0.5478   0.01933   0.01353  -0.0994   0.9358   0.0142
  -9.250  -0.5128   0.01766   0.01174  -0.1045   0.9239   0.0158
  -9.000  -0.4805   0.01678   0.01076  -0.1072   0.9108   0.0184
  -8.750  -0.4592   0.01587   0.00978  -0.1078   0.8951   0.0216
  -8.500  -0.4413   0.01511   0.00893  -0.1073   0.8802   0.0267
  -8.250  -0.4245   0.01436   0.00816  -0.1064   0.8667   0.0347
  -8.000  -0.4051   0.01374   0.00753  -0.1057   0.8547   0.0455
  -7.750  -0.3849   0.01310   0.00692  -0.1052   0.8440   0.0631
  -7.500  -0.3648   0.01246   0.00635  -0.1046   0.8332   0.0893
  -7.250  -0.3448   0.01170   0.00575  -0.1041   0.8231   0.1296
  -7.000  -0.3252   0.01071   0.00501  -0.1038   0.8139   0.1979
  -6.750  -0.3070   0.00951   0.00430  -0.1034   0.8040   0.3142
  -6.500  -0.2809   0.00925   0.00414  -0.1034   0.7958   0.3663
  -6.250  -0.2536   0.00922   0.00407  -0.1034   0.7868   0.3905
  -6.000  -0.2254   0.00926   0.00402  -0.1034   0.7789   0.4055
  -5.750  -0.1978   0.00927   0.00399  -0.1034   0.7704   0.4155
  -5.500  -0.1693   0.00933   0.00390  -0.1035   0.7627   0.4241
  -5.250  -0.1415   0.00937   0.00392  -0.1034   0.7542   0.4323
  -5.000  -0.1131   0.00947   0.00388  -0.1035   0.7469   0.4405
  -4.750  -0.0853   0.00949   0.00390  -0.1034   0.7388   0.4465
  -4.500  -0.0568   0.00962   0.00389  -0.1035   0.7315   0.4534
  -4.250  -0.0291   0.00970   0.00399  -0.1034   0.7234   0.4616
  -4.000  -0.0007   0.00983   0.00402  -0.1034   0.7163   0.4680
  -3.750   0.0275   0.00982   0.00392  -0.1036   0.7086   0.4708
  -3.500   0.0555   0.00973   0.00377  -0.1036   0.7014   0.4736
  -3.250   0.0835   0.00969   0.00371  -0.1037   0.6939   0.4762
  -3.000   0.1116   0.00968   0.00363  -0.1037   0.6866   0.4786
  -2.750   0.1399   0.00968   0.00357  -0.1038   0.6798   0.4814
  -2.500   0.1680   0.00967   0.00351  -0.1039   0.6723   0.4844
  -2.250   0.1964   0.00971   0.00343  -0.1041   0.6655   0.4870
  -2.000   0.2243   0.00963   0.00334  -0.1041   0.6582   0.4895
  -1.750   0.2523   0.00963   0.00329  -0.1042   0.6516   0.4919
  -1.500   0.2803   0.00961   0.00328  -0.1042   0.6444   0.4946
  -1.250   0.3083   0.00964   0.00325  -0.1043   0.6375   0.4975
  -1.000   0.3365   0.00967   0.00324  -0.1044   0.6309   0.5005
  -0.750   0.3645   0.00969   0.00321  -0.1045   0.6240   0.5031
  -0.500   0.3924   0.00970   0.00316  -0.1046   0.6176   0.5057
  -0.250   0.4202   0.00967   0.00317  -0.1046   0.6107   0.5083
   0.000   0.4480   0.00972   0.00318  -0.1046   0.6045   0.5112
   0.250   0.4759   0.00976   0.00321  -0.1047   0.5979   0.5144
   0.500   0.5037   0.00980   0.00322  -0.1047   0.5913   0.5175
   0.750   0.5316   0.00989   0.00324  -0.1048   0.5854   0.5203
   1.000   0.5592   0.00986   0.00325  -0.1048   0.5790   0.5233
   1.250   0.5867   0.00991   0.00329  -0.1048   0.5729   0.5262
   1.500   0.6143   0.00996   0.00335  -0.1048   0.5668   0.5294
   1.750   0.6418   0.01002   0.00341  -0.1048   0.5606   0.5330
   2.000   0.6694   0.01014   0.00347  -0.1049   0.5550   0.5364
   2.250   0.6967   0.01014   0.00353  -0.1049   0.5489   0.5397
   2.500   0.7239   0.01019   0.00360  -0.1048   0.5429   0.5431
   2.750   0.7511   0.01031   0.00369  -0.1048   0.5373   0.5466
   3.000   0.7783   0.01035   0.00378  -0.1047   0.5310   0.5504
   3.250   0.8052   0.01047   0.00385  -0.1046   0.5250   0.5541
   3.500   0.8320   0.01052   0.00397  -0.1045   0.5192   0.5582
   3.750   0.8586   0.01059   0.00408  -0.1044   0.5130   0.5624
   4.000   0.8852   0.01073   0.00419  -0.1042   0.5072   0.5669
   4.250   0.9119   0.01081   0.00431  -0.1041   0.5014   0.5711
   4.500   0.9381   0.01087   0.00444  -0.1039   0.4954   0.5755
   4.750   0.9641   0.01103   0.00459  -0.1037   0.4896   0.5803
   5.000   0.9901   0.01110   0.00472  -0.1034   0.4830   0.5858
   5.250   1.0154   0.01122   0.00486  -0.1030   0.4765   0.5910
   5.500   1.0409   0.01132   0.00503  -0.1027   0.4701   0.5966
   5.750   1.0662   0.01145   0.00518  -0.1023   0.4635   0.6027
   6.000   1.0908   0.01159   0.00536  -0.1019   0.4572   0.6085
   6.250   1.1155   0.01168   0.00554  -0.1014   0.4498   0.6152
   6.500   1.1390   0.01188   0.00572  -0.1007   0.4427   0.6223
   6.750   1.1633   0.01196   0.00592  -0.1002   0.4352   0.6300
   7.000   1.1859   0.01216   0.00612  -0.0993   0.4278   0.6383
   7.250   1.2093   0.01227   0.00635  -0.0986   0.4199   0.6471
   7.500   1.2307   0.01249   0.00657  -0.0976   0.4120   0.6563
   7.750   1.2530   0.01262   0.00681  -0.0967   0.4032   0.6667
   8.000   1.2726   0.01284   0.00707  -0.0953   0.3942   0.6777
   8.250   1.2918   0.01301   0.00732  -0.0939   0.3846   0.6903
   8.500   1.3091   0.01322   0.00760  -0.0921   0.3747   0.7045
   8.750   1.3241   0.01351   0.00793  -0.0899   0.3636   0.7203
   9.000   1.3399   0.01379   0.00829  -0.0879   0.3512   0.7385
   9.250   1.3543   0.01412   0.00869  -0.0857   0.3377   0.7600
   9.500   1.3661   0.01452   0.00915  -0.0832   0.3224   0.7868
   9.750   1.3752   0.01495   0.00968  -0.0801   0.3066   0.8255
  10.000   1.3795   0.01523   0.01016  -0.0762   0.2907   1.0000
  10.250   1.3876   0.01602   0.01088  -0.0736   0.2729   1.0000
  10.500   1.3948   0.01689   0.01168  -0.0710   0.2538   1.0000
  10.750   1.3994   0.01794   0.01265  -0.0682   0.2340   1.0000
  11.000   1.4022   0.01916   0.01378  -0.0654   0.2151   1.0000
  11.250   1.4038   0.02053   0.01506  -0.0627   0.1973   1.0000
  11.500   1.4065   0.02193   0.01640  -0.0604   0.1809   1.0000
  11.750   1.4085   0.02346   0.01788  -0.0581   0.1657   1.0000
  12.000   1.4097   0.02513   0.01951  -0.0561   0.1515   1.0000
  12.250   1.4106   0.02692   0.02126  -0.0542   0.1386   1.0000
  12.500   1.4109   0.02885   0.02315  -0.0524   0.1266   1.0000
  12.750   1.4125   0.03076   0.02505  -0.0509   0.1156   1.0000
  13.000   1.4136   0.03281   0.02710  -0.0496   0.1059   1.0000
  13.250   1.4132   0.03506   0.02933  -0.0484   0.0970   1.0000
  13.500   1.4120   0.03748   0.03174  -0.0473   0.0885   1.0000
  13.750   1.4130   0.03980   0.03409  -0.0465   0.0810   1.0000
  14.000   1.4115   0.04244   0.03672  -0.0457   0.0738   1.0000
  14.250   1.4102   0.04515   0.03946  -0.0451   0.0673   1.0000
  14.500   1.4100   0.04786   0.04220  -0.0447   0.0617   1.0000
  14.750   1.4069   0.05097   0.04531  -0.0445   0.0561   1.0000
  15.000   1.4068   0.05383   0.04822  -0.0443   0.0514   1.0000
  15.250   1.4029   0.05721   0.05162  -0.0443   0.0472   1.0000
  15.500   1.4025   0.06030   0.05477  -0.0445   0.0433   1.0000
  15.750   1.3992   0.06380   0.05829  -0.0448   0.0400   1.0000
  16.000   1.3968   0.06727   0.06183  -0.0452   0.0370   1.0000
  16.250   1.3952   0.07073   0.06534  -0.0457   0.0342   1.0000
  16.500   1.3879   0.07505   0.06969  -0.0465   0.0319   1.0000
  16.750   1.3896   0.07820   0.07293  -0.0472   0.0295   1.0000
  17.000   1.3859   0.08217   0.07695  -0.0481   0.0278   1.0000
  17.250   1.3787   0.08674   0.08158  -0.0493   0.0260   1.0000
  17.500   1.3795   0.09020   0.08513  -0.0503   0.0244   1.0000
  17.750   1.3760   0.09433   0.08933  -0.0516   0.0229   1.0000
  18.000   1.3683   0.09920   0.09424  -0.0532   0.0216   1.0000
  18.250   1.3679   0.10301   0.09815  -0.0545   0.0204   1.0000
  18.500   1.3655   0.10715   0.10237  -0.0560   0.0194   1.0000
  18.750   1.3612   0.11163   0.10691  -0.0578   0.0183   1.0000
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