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EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 553 AIRFOIL (e553-il)
Reynolds number: 100,000
Max Cl/Cd: 45.39 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e553-il-100000.txt
Download as CSV file: xf-e553-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.2381   0.14068   0.13596  -0.0460   1.0000   0.1255
 -13.750  -0.2667   0.13952   0.13486  -0.0490   1.0000   0.1312
 -13.500  -0.4546   0.10834   0.10319  -0.0645   1.0000   0.0553
 -13.250  -0.4492   0.10496   0.09985  -0.0642   1.0000   0.0543
 -13.000  -0.4627   0.09824   0.09315  -0.0667   1.0000   0.0528
 -12.750  -0.5091   0.08700   0.08184  -0.0731   1.0000   0.0504
 -12.500  -0.6136   0.07376   0.06814  -0.0824   1.0000   0.0472
 -12.250  -0.6486   0.07038   0.06458  -0.0833   1.0000   0.0466
 -12.000  -0.6593   0.06657   0.06067  -0.0828   1.0000   0.0463
 -11.750  -0.6734   0.06338   0.05742  -0.0818   1.0000   0.0460
 -11.500  -0.6916   0.06072   0.05471  -0.0799   1.0000   0.0457
 -11.250  -0.7159   0.05878   0.05272  -0.0766   1.0000   0.0455
 -11.000  -0.7408   0.05758   0.05151  -0.0721   1.0000   0.0453
 -10.750  -0.7687   0.05660   0.05049  -0.0670   1.0000   0.0452
 -10.500  -0.7898   0.05512   0.04892  -0.0627   1.0000   0.0450
 -10.250  -0.8060   0.05345   0.04712  -0.0590   1.0000   0.0447
 -10.000  -0.8191   0.05153   0.04503  -0.0557   1.0000   0.0446
  -9.750  -0.8273   0.04950   0.04279  -0.0528   1.0000   0.0445
  -9.500  -0.8314   0.04738   0.04044  -0.0502   1.0000   0.0447
  -9.250  -0.8032   0.04429   0.03683  -0.0533   0.9937   0.0458
  -9.000  -0.7733   0.04134   0.03367  -0.0557   0.9873   0.0480
  -8.750  -0.7368   0.03937   0.03165  -0.0585   0.9818   0.0512
  -8.500  -0.7041   0.03739   0.02942  -0.0599   0.9748   0.0540
  -8.250  -0.6657   0.03537   0.02747  -0.0619   0.9703   0.0591
  -8.000  -0.6373   0.03407   0.02605  -0.0629   0.9618   0.0661
  -7.750  -0.6031   0.03254   0.02464  -0.0647   0.9560   0.0770
  -7.500  -0.5817   0.03094   0.02332  -0.0648   0.9469   0.0919
  -7.250  -0.5592   0.02914   0.02173  -0.0661   0.9385   0.1180
  -7.000  -0.5417   0.02559   0.01890  -0.0692   0.9296   0.1920
  -6.750  -0.5211   0.02496   0.01942  -0.0700   0.9193   0.4069
  -6.500  -0.4764   0.02749   0.02187  -0.0703   0.9130   0.4453
  -6.250  -0.4489   0.02938   0.02371  -0.0682   0.9034   0.4642
  -6.000  -0.4051   0.03166   0.02594  -0.0678   0.8978   0.4829
  -5.750  -0.3741   0.03370   0.02795  -0.0653   0.8899   0.4951
  -5.500  -0.3356   0.03517   0.02933  -0.0645   0.8834   0.5087
  -5.250  -0.2857   0.03630   0.03031  -0.0658   0.8803   0.5234
  -5.000  -0.2648   0.03749   0.03146  -0.0624   0.8703   0.5323
  -4.750  -0.2162   0.03824   0.03208  -0.0633   0.8666   0.5435
  -4.500  -0.1692   0.03745   0.03108  -0.0674   0.8633   0.5562
  -4.250  -0.1539   0.03783   0.03142  -0.0641   0.8524   0.5614
  -4.000  -0.1151   0.03612   0.02948  -0.0690   0.8478   0.5719
  -3.750  -0.0991   0.03630   0.02962  -0.0662   0.8375   0.5757
  -3.500  -0.0596   0.03536   0.02853  -0.0692   0.8326   0.5823
  -3.250  -0.0466   0.03426   0.02729  -0.0696   0.8221   0.5887
  -3.000  -0.0087   0.03391   0.02685  -0.0706   0.8170   0.5925
  -2.750   0.0155   0.03335   0.02619  -0.0710   0.8093   0.5973
  -2.500   0.0439   0.03200   0.02463  -0.0744   0.8013   0.6040
  -2.250   0.0847   0.03151   0.02407  -0.0758   0.7976   0.6071
  -2.000   0.0944   0.03147   0.02400  -0.0736   0.7864   0.6102
  -1.750   0.1348   0.03066   0.02305  -0.0765   0.7821   0.6151
  -1.500   0.1510   0.03018   0.02245  -0.0770   0.7715   0.6206
  -1.250   0.1867   0.02970   0.02192  -0.0780   0.7667   0.6234
  -1.000   0.2026   0.02974   0.02194  -0.0766   0.7574   0.6266
  -0.750   0.2370   0.02925   0.02135  -0.0783   0.7516   0.6314
  -0.500   0.2673   0.02879   0.02076  -0.0803   0.7447   0.6370
  -0.250   0.2898   0.02872   0.02070  -0.0795   0.7369   0.6398
   0.000   0.3279   0.02824   0.02016  -0.0811   0.7328   0.6435
   0.250   0.3403   0.02854   0.02046  -0.0796   0.7225   0.6479
   0.500   0.3808   0.02796   0.01975  -0.0825   0.7178   0.6538
   0.750   0.3943   0.02832   0.02017  -0.0805   0.7090   0.6569
   1.000   0.4258   0.02809   0.01991  -0.0812   0.7032   0.6609
   1.250   0.4677   0.02756   0.01929  -0.0838   0.6996   0.6663
   1.500   0.4772   0.02816   0.01992  -0.0820   0.6890   0.6710
   1.750   0.5125   0.02782   0.01958  -0.0829   0.6849   0.6754
   2.000   0.5240   0.02844   0.02026  -0.0811   0.6755   0.6801
   2.250   0.5616   0.02814   0.01988  -0.0834   0.6704   0.6861
   2.500   0.5887   0.02815   0.01993  -0.0831   0.6651   0.6903
   2.750   0.6023   0.02872   0.02059  -0.0815   0.6564   0.6955
   3.000   0.6442   0.02829   0.02009  -0.0840   0.6524   0.7026
   3.250   0.6482   0.02927   0.02121  -0.0809   0.6431   0.7069
   3.500   0.6825   0.02905   0.02101  -0.0819   0.6382   0.7130
   3.750   0.7263   0.02855   0.02047  -0.0844   0.6349   0.7201
   4.000   0.7223   0.02990   0.02198  -0.0804   0.6242   0.7253
   4.250   0.7644   0.02942   0.02150  -0.0825   0.6204   0.7337
   4.500   0.7640   0.03071   0.02293  -0.0791   0.6107   0.7394
   4.750   0.8007   0.03036   0.02261  -0.0803   0.6060   0.7474
   5.000   0.8454   0.02969   0.02196  -0.0823   0.6027   0.7558
   5.250   0.8365   0.03138   0.02383  -0.0780   0.5917   0.7637
   5.500   0.8804   0.03063   0.02311  -0.0798   0.5880   0.7735
   5.750   0.8744   0.03232   0.02496  -0.0760   0.5776   0.7832
   6.000   0.9140   0.03164   0.02435  -0.0771   0.5734   0.7938
   6.250   0.9170   0.03283   0.02568  -0.0742   0.5647   0.8048
   6.500   0.9476   0.03259   0.02554  -0.0742   0.5587   0.8187
   6.750   0.9980   0.03135   0.02434  -0.0764   0.5551   0.8351
   7.000   0.9781   0.03333   0.02655  -0.0705   0.5440   0.8516
   7.250   1.0274   0.03184   0.02513  -0.0721   0.5400   0.8746
   7.500   1.0044   0.03364   0.02719  -0.0656   0.5295   0.9082
   7.750   1.0765   0.03159   0.02522  -0.0711   0.5244   1.0000
   8.000   1.0913   0.03289   0.02660  -0.0714   0.5138   1.0000
   8.250   1.1641   0.03112   0.02475  -0.0773   0.5075   1.0000
   8.500   1.1682   0.03237   0.02611  -0.0751   0.4966   1.0000
   8.750   1.2208   0.03127   0.02498  -0.0781   0.4884   1.0000
   9.000   1.2423   0.03142   0.02518  -0.0773   0.4779   1.0000
   9.250   1.2584   0.03179   0.02562  -0.0757   0.4674   1.0000
   9.500   1.3054   0.03076   0.02455  -0.0778   0.4571   1.0000
   9.750   1.3226   0.03087   0.02472  -0.0761   0.4455   1.0000
  10.000   1.3330   0.03124   0.02518  -0.0735   0.4336   1.0000
  10.250   1.3536   0.03111   0.02508  -0.0722   0.4213   1.0000
  10.500   1.3757   0.03086   0.02481  -0.0709   0.4083   1.0000
  10.750   1.3935   0.03070   0.02465  -0.0691   0.3947   1.0000
  11.000   1.3964   0.03109   0.02507  -0.0654   0.3813   1.0000
  11.250   1.3932   0.03182   0.02589  -0.0613   0.3677   1.0000
  11.500   1.3923   0.03258   0.02668  -0.0578   0.3534   1.0000
  11.750   1.3911   0.03350   0.02762  -0.0546   0.3384   1.0000
  12.000   1.3885   0.03463   0.02876  -0.0516   0.3228   1.0000
  12.250   1.3846   0.03603   0.03014  -0.0487   0.3068   1.0000
  12.500   1.3801   0.03766   0.03175  -0.0462   0.2903   1.0000
  12.750   1.3757   0.03948   0.03349  -0.0440   0.2735   1.0000
  13.000   1.3699   0.04161   0.03555  -0.0420   0.2568   1.0000
  13.250   1.3618   0.04415   0.03804  -0.0402   0.2405   1.0000
  13.500   1.3543   0.04682   0.04067  -0.0387   0.2247   1.0000
  13.750   1.3472   0.04963   0.04343  -0.0376   0.2095   1.0000
  14.000   1.3409   0.05254   0.04627  -0.0366   0.1949   1.0000
  14.250   1.3355   0.05551   0.04916  -0.0359   0.1811   1.0000
  14.500   1.3317   0.05844   0.05199  -0.0353   0.1679   1.0000
  14.750   1.3249   0.06185   0.05543  -0.0350   0.1561   1.0000
  15.000   1.3195   0.06528   0.05889  -0.0348   0.1448   1.0000
  15.250   1.3166   0.06854   0.06214  -0.0347   0.1342   1.0000
  15.500   1.3165   0.07149   0.06500  -0.0346   0.1241   1.0000
  15.750   1.3129   0.07498   0.06853  -0.0349   0.1155   1.0000
  16.000   1.3103   0.07852   0.07214  -0.0351   0.1074   1.0000
  16.250   1.3166   0.08088   0.07433  -0.0350   0.0990   1.0000
  16.500   1.3086   0.08527   0.07896  -0.0359   0.0932   1.0000
  16.750   1.3164   0.08756   0.08112  -0.0358   0.0862   1.0000
  17.000   1.3085   0.09210   0.08592  -0.0369   0.0818   1.0000
  17.250   1.3224   0.09362   0.08722  -0.0365   0.0753   1.0000
  17.500   1.3109   0.09881   0.09274  -0.0382   0.0725   1.0000
  17.750   1.3061   0.10305   0.09714  -0.0395   0.0689   1.0000
  18.000   1.3198   0.10469   0.09864  -0.0392   0.0642   1.0000
  18.250   1.3051   0.11055   0.10483  -0.0416   0.0625   1.0000
  18.500   1.2930   0.11617   0.11071  -0.0440   0.0606   1.0000
  18.750   1.2834   0.12145   0.11617  -0.0464   0.0587   1.0000
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