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EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 552 AIRFOIL (e552-il)
Reynolds number: 500,000
Max Cl/Cd: 106.33 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e552-il-500000.txt
Download as CSV file: xf-e552-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6635   0.10124   0.09812  -0.0493   1.0000   0.0095
 -16.000  -0.6796   0.09404   0.09079  -0.0535   1.0000   0.0094
 -15.750  -0.6923   0.08792   0.08454  -0.0570   1.0000   0.0094
 -15.500  -0.7031   0.08261   0.07913  -0.0593   1.0000   0.0093
 -15.250  -0.7220   0.07611   0.07245  -0.0629   1.0000   0.0093
 -15.000  -0.7347   0.07099   0.06719  -0.0651   1.0000   0.0093
 -14.750  -0.7477   0.06604   0.06208  -0.0672   1.0000   0.0093
 -14.500  -0.7572   0.06184   0.05773  -0.0689   1.0000   0.0093
 -14.250  -0.7649   0.05801   0.05377  -0.0699   1.0000   0.0092
 -14.000  -0.7729   0.05453   0.05012  -0.0712   1.0000   0.0093
 -13.750  -0.7774   0.05133   0.04679  -0.0714   1.0000   0.0093
 -13.500  -0.7812   0.04850   0.04381  -0.0720   1.0000   0.0094
 -13.250  -0.7802   0.04603   0.04124  -0.0717   1.0000   0.0093
 -13.000  -0.7817   0.04350   0.03856  -0.0716   1.0000   0.0094
 -12.750  -0.7788   0.04137   0.03632  -0.0710   1.0000   0.0095
 -12.500  -0.7751   0.03935   0.03421  -0.0699   1.0000   0.0096
 -12.250  -0.7699   0.03763   0.03243  -0.0688   1.0000   0.0097
 -12.000  -0.7645   0.03604   0.03081  -0.0678   1.0000   0.0098
 -11.750  -0.7590   0.03452   0.02925  -0.0666   1.0000   0.0099
 -11.500  -0.7537   0.03310   0.02779  -0.0654   1.0000   0.0101
 -11.250  -0.7486   0.03175   0.02642  -0.0641   1.0000   0.0102
 -11.000  -0.7444   0.03045   0.02509  -0.0626   1.0000   0.0104
 -10.500  -0.7022   0.02738   0.02193  -0.0659   0.9781   0.0109
 -10.250  -0.6611   0.02564   0.02011  -0.0714   0.9454   0.0113
 -10.000  -0.5897   0.02353   0.01785  -0.0833   0.9225   0.0123
  -9.750  -0.5277   0.02133   0.01544  -0.0944   0.8730   0.0135
  -9.500  -0.5144   0.02029   0.01415  -0.0943   0.8258   0.0140
  -9.250  -0.5106   0.01926   0.01292  -0.0923   0.7946   0.0147
  -9.000  -0.5098   0.01842   0.01191  -0.0896   0.7704   0.0150
  -8.750  -0.5058   0.01747   0.01079  -0.0873   0.7511   0.0159
  -8.500  -0.4933   0.01680   0.01002  -0.0857   0.7345   0.0171
  -8.250  -0.4773   0.01621   0.00931  -0.0845   0.7198   0.0193
  -8.000  -0.4612   0.01553   0.00857  -0.0833   0.7066   0.0224
  -7.750  -0.4429   0.01490   0.00789  -0.0824   0.6947   0.0281
  -7.500  -0.4238   0.01429   0.00724  -0.0815   0.6838   0.0375
  -7.250  -0.4028   0.01373   0.00670  -0.0810   0.6732   0.0515
  -7.000  -0.3814   0.01314   0.00618  -0.0805   0.6637   0.0744
  -6.750  -0.3601   0.01249   0.00565  -0.0801   0.6546   0.1093
  -6.500  -0.3388   0.01165   0.00505  -0.0799   0.6458   0.1666
  -6.250  -0.3201   0.01038   0.00422  -0.0796   0.6380   0.2792
  -6.000  -0.2966   0.00970   0.00395  -0.0796   0.6301   0.3874
  -5.750  -0.2687   0.00973   0.00391  -0.0797   0.6229   0.4170
  -5.500  -0.2403   0.00979   0.00392  -0.0797   0.6162   0.4339
  -5.250  -0.2118   0.00987   0.00392  -0.0798   0.6096   0.4452
  -5.000  -0.1835   0.00995   0.00390  -0.0799   0.6039   0.4530
  -4.750  -0.1546   0.01004   0.00391  -0.0800   0.5979   0.4614
  -4.500  -0.1262   0.01013   0.00395  -0.0800   0.5924   0.4693
  -4.250  -0.0976   0.01025   0.00397  -0.0801   0.5872   0.4759
  -4.000  -0.0688   0.01028   0.00394  -0.0803   0.5820   0.4816
  -3.750  -0.0404   0.01048   0.00413  -0.0803   0.5773   0.4907
  -3.500  -0.0119   0.01064   0.00417  -0.0803   0.5730   0.4979
  -3.250   0.0169   0.01058   0.00412  -0.0805   0.5690   0.5004
  -3.000   0.0458   0.01056   0.00406  -0.0807   0.5649   0.5026
  -2.750   0.0746   0.01056   0.00399  -0.0810   0.5611   0.5049
  -2.500   0.1034   0.01061   0.00393  -0.0812   0.5574   0.5073
  -2.250   0.1324   0.01058   0.00387  -0.0815   0.5539   0.5094
  -2.000   0.1615   0.01058   0.00381  -0.0817   0.5502   0.5113
  -1.750   0.1902   0.01052   0.00372  -0.0820   0.5469   0.5135
  -1.500   0.2189   0.01052   0.00369  -0.0822   0.5438   0.5157
  -1.250   0.2479   0.01058   0.00370  -0.0825   0.5408   0.5178
  -1.000   0.2767   0.01057   0.00369  -0.0827   0.5381   0.5200
  -0.750   0.3056   0.01057   0.00368  -0.0830   0.5350   0.5222
  -0.500   0.3345   0.01059   0.00367  -0.0832   0.5320   0.5246
  -0.250   0.3635   0.01064   0.00366  -0.0835   0.5292   0.5269
   0.000   0.3924   0.01069   0.00366  -0.0838   0.5266   0.5293
   0.250   0.4212   0.01072   0.00371  -0.0841   0.5241   0.5318
   0.500   0.4499   0.01073   0.00375  -0.0843   0.5217   0.5341
   0.750   0.4786   0.01075   0.00379  -0.0845   0.5189   0.5367
   1.000   0.5073   0.01079   0.00382  -0.0847   0.5162   0.5394
   1.250   0.5362   0.01085   0.00386  -0.0850   0.5139   0.5421
   1.500   0.5652   0.01095   0.00391  -0.0853   0.5115   0.5446
   1.750   0.5940   0.01103   0.00401  -0.0856   0.5090   0.5476
   2.000   0.6223   0.01105   0.00409  -0.0858   0.5067   0.5506
   2.250   0.6507   0.01110   0.00418  -0.0860   0.5043   0.5538
   2.500   0.6792   0.01116   0.00426  -0.0862   0.5017   0.5571
   2.750   0.7079   0.01123   0.00432  -0.0865   0.4992   0.5602
   3.000   0.7363   0.01128   0.00440  -0.0867   0.4968   0.5635
   3.250   0.7652   0.01144   0.00455  -0.0870   0.4941   0.5669
   3.500   0.7931   0.01149   0.00467  -0.0871   0.4918   0.5706
   3.750   0.8210   0.01155   0.00478  -0.0872   0.4890   0.5747
   4.000   0.8489   0.01159   0.00487  -0.0873   0.4859   0.5787
   4.250   0.8769   0.01163   0.00496  -0.0874   0.4829   0.5830
   4.500   0.9051   0.01173   0.00507  -0.0876   0.4800   0.5875
   4.750   0.9333   0.01189   0.00524  -0.0878   0.4770   0.5923
   5.000   0.9602   0.01190   0.00537  -0.0878   0.4740   0.5968
   5.250   0.9874   0.01194   0.00548  -0.0878   0.4705   0.6019
   5.500   1.0148   0.01199   0.00556  -0.0878   0.4669   0.6076
   5.750   1.0426   0.01211   0.00569  -0.0879   0.4633   0.6131
   6.000   1.0690   0.01217   0.00586  -0.0878   0.4598   0.6194
   6.250   1.0955   0.01221   0.00598  -0.0876   0.4558   0.6264
   6.500   1.1220   0.01224   0.00610  -0.0875   0.4518   0.6333
   6.750   1.1491   0.01237   0.00622  -0.0875   0.4477   0.6413
   7.000   1.1744   0.01239   0.00640  -0.0871   0.4432   0.6489
   7.250   1.2000   0.01243   0.00652  -0.0868   0.4382   0.6579
   7.500   1.2254   0.01248   0.00664  -0.0865   0.4331   0.6670
   7.750   1.2504   0.01255   0.00682  -0.0861   0.4277   0.6772
   8.000   1.2750   0.01259   0.00696  -0.0857   0.4215   0.6889
   8.250   1.2990   0.01269   0.00713  -0.0851   0.4154   0.7013
   8.500   1.3229   0.01272   0.00732  -0.0845   0.4077   0.7153
   8.750   1.3455   0.01283   0.00750  -0.0837   0.3999   0.7307
   9.000   1.3677   0.01292   0.00771  -0.0828   0.3895   0.7482
   9.250   1.3887   0.01306   0.00795  -0.0818   0.3776   0.7684
   9.500   1.4071   0.01325   0.00823  -0.0802   0.3628   0.7922
   9.750   1.4214   0.01354   0.00858  -0.0780   0.3446   0.8237
  10.000   1.4282   0.01386   0.00899  -0.0743   0.3257   0.8775
  10.250   1.4336   0.01428   0.00944  -0.0705   0.3047   1.0000
  10.500   1.4380   0.01508   0.01013  -0.0671   0.2838   1.0000
  10.750   1.4420   0.01595   0.01093  -0.0638   0.2642   1.0000
  11.000   1.4440   0.01695   0.01186  -0.0604   0.2456   1.0000
  11.250   1.4442   0.01811   0.01297  -0.0571   0.2289   1.0000
  11.500   1.4426   0.01948   0.01429  -0.0541   0.2132   1.0000
  11.750   1.4390   0.02114   0.01590  -0.0512   0.1979   1.0000
  12.000   1.4363   0.02295   0.01769  -0.0489   0.1845   1.0000
  12.250   1.4321   0.02506   0.01977  -0.0469   0.1714   1.0000
  12.500   1.4265   0.02748   0.02216  -0.0452   0.1585   1.0000
  12.750   1.4201   0.03013   0.02479  -0.0438   0.1464   1.0000
  13.000   1.4143   0.03289   0.02755  -0.0427   0.1366   1.0000
  13.250   1.4076   0.03582   0.03046  -0.0418   0.1258   1.0000
  13.500   1.4034   0.03863   0.03328  -0.0411   0.1165   1.0000
  13.750   1.3973   0.04168   0.03633  -0.0405   0.1077   1.0000
  14.000   1.3913   0.04482   0.03946  -0.0400   0.0998   1.0000
  14.250   1.3880   0.04779   0.04245  -0.0398   0.0923   1.0000
  14.500   1.3826   0.05108   0.04575  -0.0397   0.0856   1.0000
  14.750   1.3818   0.05398   0.04868  -0.0397   0.0796   1.0000
  15.000   1.3772   0.05736   0.05206  -0.0398   0.0737   1.0000
  15.250   1.3765   0.06039   0.05513  -0.0400   0.0683   1.0000
  15.500   1.3725   0.06388   0.05862  -0.0404   0.0626   1.0000
  15.750   1.3724   0.06697   0.06175  -0.0408   0.0580   1.0000
  16.000   1.3677   0.07070   0.06549  -0.0414   0.0535   1.0000
  16.250   1.3690   0.07374   0.06859  -0.0419   0.0494   1.0000
  16.500   1.3650   0.07754   0.07238  -0.0427   0.0453   1.0000
  16.750   1.3652   0.08083   0.07573  -0.0434   0.0419   1.0000
  17.000   1.3633   0.08446   0.07939  -0.0443   0.0387   1.0000
  17.250   1.3584   0.08860   0.08357  -0.0454   0.0361   1.0000
  17.500   1.3611   0.09170   0.08673  -0.0463   0.0334   1.0000
  17.750   1.3582   0.09567   0.09076  -0.0475   0.0315   1.0000
  18.000   1.3535   0.09995   0.09507  -0.0489   0.0293   1.0000
  18.250   1.3550   0.10335   0.09855  -0.0501   0.0273   1.0000
  18.500   1.3526   0.10739   0.10263  -0.0516   0.0253   1.0000
  18.750   1.3469   0.11200   0.10730  -0.0533   0.0237   1.0000
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