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EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 500,000
Max Cl/Cd: 99.6 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e550-il-500000.txt
Download as CSV file: xf-e550-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 550 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6287   0.08307   0.08012  -0.0557   1.0000   0.0096
 -14.250  -0.6478   0.07636   0.07330  -0.0592   1.0000   0.0095
 -14.000  -0.6693   0.06993   0.06671  -0.0622   1.0000   0.0094
 -13.750  -0.6920   0.06394   0.06055  -0.0645   1.0000   0.0094
 -13.500  -0.7079   0.05936   0.05582  -0.0657   1.0000   0.0093
 -13.250  -0.7243   0.05494   0.05124  -0.0665   1.0000   0.0092
 -13.000  -0.7378   0.05104   0.04716  -0.0667   1.0000   0.0090
 -12.750  -0.7501   0.04738   0.04332  -0.0665   1.0000   0.0089
 -12.500  -0.7594   0.04417   0.03991  -0.0658   1.0000   0.0088
 -12.250  -0.7683   0.04092   0.03643  -0.0647   1.0000   0.0087
 -12.000  -0.7721   0.03829   0.03359  -0.0634   1.0000   0.0087
 -11.750  -0.7719   0.03598   0.03109  -0.0619   1.0000   0.0086
 -11.500  -0.7707   0.03401   0.02894  -0.0603   1.0000   0.0090
 -11.250  -0.7649   0.03233   0.02713  -0.0586   1.0000   0.0089
 -11.000  -0.7571   0.03086   0.02555  -0.0570   1.0000   0.0088
 -10.750  -0.7503   0.02954   0.02410  -0.0551   1.0000   0.0091
 -10.500  -0.7436   0.02834   0.02279  -0.0531   1.0000   0.0094
 -10.250  -0.7097   0.02680   0.02111  -0.0557   0.9937   0.0096
 -10.000  -0.6819   0.02531   0.01951  -0.0570   0.9574   0.0098
  -9.750  -0.6192   0.02342   0.01757  -0.0655   0.9334   0.0103
  -9.500  -0.5313   0.02173   0.01572  -0.0796   0.8969   0.0114
  -9.250  -0.4970   0.02084   0.01452  -0.0825   0.8375   0.0119
  -9.000  -0.4858   0.02018   0.01365  -0.0808   0.8011   0.0121
  -8.750  -0.4807   0.01923   0.01255  -0.0784   0.7743   0.0127
  -8.500  -0.4724   0.01847   0.01168  -0.0764   0.7530   0.0135
  -8.250  -0.4627   0.01780   0.01091  -0.0744   0.7350   0.0142
  -8.000  -0.4522   0.01724   0.01022  -0.0723   0.7194   0.0153
  -7.750  -0.4523   0.01649   0.00939  -0.0687   0.7056   0.0164
  -7.500  -0.4391   0.01602   0.00882  -0.0668   0.6930   0.0178
  -7.250  -0.4262   0.01541   0.00816  -0.0649   0.6811   0.0199
  -7.000  -0.4104   0.01488   0.00756  -0.0633   0.6703   0.0233
  -6.500  -0.3766   0.01374   0.00643  -0.0606   0.6508   0.0445
  -6.250  -0.3586   0.01316   0.00594  -0.0595   0.6424   0.0685
  -6.000  -0.3391   0.01256   0.00548  -0.0587   0.6341   0.1036
  -5.750  -0.3202   0.01190   0.00500  -0.0578   0.6268   0.1570
  -5.500  -0.3035   0.01078   0.00435  -0.0570   0.6197   0.2602
  -5.250  -0.2902   0.00920   0.00360  -0.0559   0.6132   0.4569
  -5.000  -0.2634   0.00920   0.00368  -0.0558   0.6068   0.5194
  -4.750  -0.2352   0.00933   0.00376  -0.0558   0.6002   0.5411
  -4.500  -0.2070   0.00952   0.00382  -0.0558   0.5942   0.5548
  -4.250  -0.1784   0.00965   0.00391  -0.0558   0.5885   0.5639
  -4.000  -0.1499   0.00977   0.00394  -0.0559   0.5831   0.5716
  -3.750  -0.1215   0.00999   0.00408  -0.0558   0.5782   0.5793
  -3.500  -0.0928   0.01012   0.00413  -0.0560   0.5737   0.5864
  -3.250  -0.0643   0.01036   0.00440  -0.0558   0.5690   0.5945
  -3.000  -0.0361   0.01066   0.00465  -0.0556   0.5647   0.6047
  -2.750  -0.0077   0.01088   0.00483  -0.0556   0.5604   0.6096
  -2.500   0.0211   0.01084   0.00475  -0.0559   0.5564   0.6118
  -2.250   0.0500   0.01081   0.00466  -0.0562   0.5524   0.6137
  -2.000   0.0788   0.01080   0.00456  -0.0565   0.5488   0.6155
  -1.750   0.1077   0.01085   0.00449  -0.0568   0.5454   0.6172
  -1.500   0.1367   0.01083   0.00441  -0.0572   0.5422   0.6186
  -1.250   0.1654   0.01074   0.00431  -0.0575   0.5390   0.6199
  -1.000   0.1941   0.01070   0.00426  -0.0578   0.5356   0.6213
  -0.750   0.2228   0.01071   0.00423  -0.0580   0.5325   0.6228
  -0.500   0.2516   0.01076   0.00422  -0.0583   0.5294   0.6243
  -0.250   0.2805   0.01080   0.00423  -0.0587   0.5266   0.6257
   0.000   0.3094   0.01079   0.00422  -0.0590   0.5240   0.6272
   0.250   0.3382   0.01080   0.00421  -0.0593   0.5212   0.6288
   0.500   0.3671   0.01082   0.00420  -0.0597   0.5183   0.6304
   0.750   0.3959   0.01086   0.00420  -0.0600   0.5155   0.6321
   1.000   0.4250   0.01097   0.00423  -0.0604   0.5129   0.6338
   1.250   0.4540   0.01104   0.00428  -0.0608   0.5105   0.6352
   1.500   0.4824   0.01100   0.00428  -0.0611   0.5080   0.6367
   1.750   0.5109   0.01100   0.00431  -0.0613   0.5053   0.6382
   2.000   0.5394   0.01103   0.00436  -0.0616   0.5027   0.6397
   2.250   0.5681   0.01109   0.00441  -0.0619   0.5003   0.6413
   2.500   0.5968   0.01117   0.00448  -0.0622   0.4977   0.6430
   2.750   0.6257   0.01132   0.00461  -0.0626   0.4951   0.6448
   3.000   0.6538   0.01135   0.00469  -0.0628   0.4928   0.6469
   3.250   0.6821   0.01140   0.00477  -0.0631   0.4900   0.6490
   3.500   0.7105   0.01146   0.00483  -0.0633   0.4871   0.6508
   3.750   0.7388   0.01150   0.00488  -0.0636   0.4843   0.6525
   4.000   0.7670   0.01157   0.00495  -0.0639   0.4814   0.6544
   4.250   0.7952   0.01169   0.00510  -0.0641   0.4784   0.6563
   4.500   0.8225   0.01171   0.00520  -0.0642   0.4754   0.6582
   4.750   0.8501   0.01175   0.00530  -0.0643   0.4720   0.6604
   5.000   0.8779   0.01180   0.00538  -0.0644   0.4687   0.6627
   5.250   0.9058   0.01190   0.00547  -0.0646   0.4655   0.6650
   5.500   0.9336   0.01204   0.00563  -0.0648   0.4620   0.6674
   5.750   0.9601   0.01204   0.00573  -0.0647   0.4582   0.6699
   6.000   0.9869   0.01206   0.00582  -0.0647   0.4542   0.6724
   6.250   1.0138   0.01211   0.00590  -0.0647   0.4502   0.6749
   6.500   1.0408   0.01224   0.00606  -0.0647   0.4462   0.6776
   6.750   1.0666   0.01226   0.00619  -0.0645   0.4416   0.6804
   7.000   1.0929   0.01231   0.00628  -0.0644   0.4369   0.6834
   7.250   1.1193   0.01242   0.00639  -0.0644   0.4322   0.6862
   7.500   1.1442   0.01243   0.00655  -0.0640   0.4270   0.6891
   7.750   1.1692   0.01246   0.00666  -0.0636   0.4209   0.6923
   8.000   1.1940   0.01258   0.00680  -0.0633   0.4149   0.6959
   8.250   1.2185   0.01262   0.00695  -0.0629   0.4072   0.6999
   8.500   1.2419   0.01273   0.00709  -0.0623   0.3996   0.7037
   8.750   1.2654   0.01280   0.00727  -0.0617   0.3900   0.7077
   9.000   1.2878   0.01294   0.00747  -0.0609   0.3792   0.7121
   9.250   1.3088   0.01314   0.00770  -0.0600   0.3661   0.7168
   9.500   1.3279   0.01339   0.00797  -0.0587   0.3499   0.7214
   9.750   1.3434   0.01377   0.00834  -0.0568   0.3294   0.7264
  10.000   1.3540   0.01432   0.00882  -0.0542   0.3063   0.7322
  10.250   1.3582   0.01495   0.00939  -0.0505   0.2833   0.7380
  10.500   1.3610   0.01572   0.01011  -0.0468   0.2628   0.7448
  10.750   1.3634   0.01657   0.01092  -0.0432   0.2430   0.7524
  11.000   1.3636   0.01753   0.01187  -0.0396   0.2251   0.7611
  11.250   1.3619   0.01865   0.01298  -0.0360   0.2088   0.7713
  11.750   1.3549   0.02146   0.01584  -0.0298   0.1794   0.7987
  12.000   1.3501   0.02316   0.01761  -0.0271   0.1664   0.8189
  12.250   1.3442   0.02500   0.01957  -0.0246   0.1549   0.8526
  12.500   1.3410   0.02704   0.02181  -0.0233   0.1429   1.0000
  12.750   1.3360   0.02959   0.02433  -0.0221   0.1320   1.0000
  13.000   1.3321   0.03217   0.02689  -0.0213   0.1219   1.0000
  13.250   1.3289   0.03476   0.02949  -0.0206   0.1127   1.0000
  13.500   1.3238   0.03761   0.03232  -0.0200   0.1044   1.0000
  13.750   1.3191   0.04048   0.03519  -0.0195   0.0964   1.0000
  14.000   1.3157   0.04330   0.03803  -0.0192   0.0890   1.0000
  14.250   1.3097   0.04647   0.04119  -0.0190   0.0820   1.0000
  14.500   1.3077   0.04934   0.04409  -0.0189   0.0753   1.0000
  14.750   1.3041   0.05246   0.04722  -0.0190   0.0696   1.0000
  15.000   1.3012   0.05560   0.05037  -0.0192   0.0636   1.0000
  15.250   1.2996   0.05866   0.05345  -0.0195   0.0587   1.0000
  15.500   1.2964   0.06199   0.05679  -0.0200   0.0538   1.0000
  15.750   1.2952   0.06517   0.06001  -0.0205   0.0496   1.0000
  16.000   1.2929   0.06853   0.06338  -0.0211   0.0454   1.0000
  16.250   1.2916   0.07186   0.06676  -0.0218   0.0421   1.0000
  16.500   1.2904   0.07523   0.07015  -0.0226   0.0388   1.0000
  16.750   1.2874   0.07891   0.07387  -0.0235   0.0360   1.0000
  17.000   1.2876   0.08223   0.07725  -0.0245   0.0332   1.0000
  17.250   1.2827   0.08629   0.08133  -0.0257   0.0307   1.0000
  17.500   1.2840   0.08958   0.08470  -0.0267   0.0285   1.0000
  17.750   1.2819   0.09339   0.08854  -0.0280   0.0266   1.0000
  18.000   1.2780   0.09754   0.09275  -0.0295   0.0248   1.0000
  18.250   1.2788   0.10102   0.09630  -0.0308   0.0230   1.0000
  18.500   1.2745   0.10534   0.10066  -0.0325   0.0216   1.0000
  18.750   1.2713   0.10955   0.10495  -0.0342   0.0203   1.0000
  19.000   1.2709   0.11337   0.10885  -0.0358   0.0190   1.0000
  19.250   1.2666   0.11785   0.11338  -0.0378   0.0178   1.0000
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