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EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 50,000
Max Cl/Cd: 11.14 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e550-il-50000-n5.txt
Download as CSV file: xf-e550-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4821   0.10071   0.09344  -0.0549   1.0000   0.0380
 -12.750  -0.4981   0.09422   0.08692  -0.0582   1.0000   0.0377
 -12.500  -0.5157   0.08822   0.08087  -0.0612   1.0000   0.0374
 -12.250  -0.5379   0.08227   0.07482  -0.0639   1.0000   0.0372
 -12.000  -0.5572   0.07722   0.06966  -0.0657   1.0000   0.0370
 -11.750  -0.5758   0.07270   0.06500  -0.0667   1.0000   0.0369
 -11.500  -0.5934   0.06859   0.06074  -0.0671   1.0000   0.0368
 -11.250  -0.6090   0.06498   0.05695  -0.0668   1.0000   0.0369
 -11.000  -0.6220   0.06181   0.05360  -0.0658   1.0000   0.0370
 -10.750  -0.6333   0.05888   0.05047  -0.0644   1.0000   0.0372
 -10.500  -0.6456   0.05623   0.04758  -0.0622   1.0000   0.0377
 -10.250  -0.6510   0.05400   0.04524  -0.0599   1.0000   0.0385
 -10.000  -0.6501   0.05233   0.04359  -0.0578   1.0000   0.0396
  -9.750  -0.6500   0.05068   0.04189  -0.0554   1.0000   0.0407
  -9.500  -0.6486   0.04895   0.04004  -0.0528   1.0000   0.0420
  -9.250  -0.6445   0.04724   0.03815  -0.0502   1.0000   0.0434
  -9.000  -0.6381   0.04579   0.03649  -0.0475   1.0000   0.0447
  -8.750  -0.6059   0.04403   0.03475  -0.0481   0.9957   0.0477
  -8.500  -0.5477   0.04230   0.03283  -0.0507   0.9881   0.0547
  -8.250  -0.4988   0.04110   0.03153  -0.0524   0.9723   0.0637
  -8.000  -0.4612   0.03979   0.03023  -0.0541   0.9528   0.0748
  -7.750  -0.4290   0.03810   0.02866  -0.0563   0.9339   0.0905
  -7.500  -0.4004   0.03615   0.02682  -0.0589   0.9154   0.1149
  -7.250  -0.3821   0.03380   0.02479  -0.0609   0.8959   0.1504
  -7.000  -0.3776   0.03132   0.02274  -0.0613   0.8748   0.2051
  -6.750  -0.3802   0.02941   0.02180  -0.0591   0.8551   0.3110
  -6.500  -0.3353   0.03308   0.02591  -0.0553   0.8413   0.4906
  -6.250  -0.3209   0.03371   0.02620  -0.0532   0.8251   0.5321
  -6.000  -0.2936   0.03525   0.02739  -0.0510   0.8115   0.5625
  -5.750  -0.2754   0.03605   0.02791  -0.0485   0.7978   0.5864
  -5.500  -0.2338   0.03784   0.02936  -0.0470   0.7865   0.6059
  -5.250  -0.1986   0.03871   0.02991  -0.0460   0.7765   0.6230
  -5.000  -0.1788   0.03885   0.02983  -0.0444   0.7652   0.6373
  -4.750  -0.1501   0.03893   0.02963  -0.0438   0.7558   0.6474
  -4.500  -0.1283   0.03868   0.02916  -0.0430   0.7466   0.6561
  -4.250  -0.1104   0.03839   0.02868  -0.0419   0.7375   0.6646
  -4.000  -0.0918   0.03799   0.02808  -0.0409   0.7295   0.6717
  -3.750  -0.0693   0.03776   0.02767  -0.0403   0.7215   0.6776
  -3.500  -0.0632   0.03719   0.02697  -0.0384   0.7141   0.6859
  -3.250  -0.0345   0.03698   0.02656  -0.0385   0.7077   0.6897
  -3.000  -0.0167   0.03672   0.02619  -0.0376   0.7002   0.6950
  -2.750  -0.0080   0.03613   0.02544  -0.0361   0.6945   0.7020
  -2.500   0.0151   0.03602   0.02524  -0.0357   0.6875   0.7052
  -2.250   0.0362   0.03579   0.02488  -0.0351   0.6815   0.7091
  -2.000   0.0553   0.03541   0.02435  -0.0346   0.6770   0.7138
  -1.750   0.0615   0.03518   0.02408  -0.0327   0.6703   0.7189
  -1.500   0.0841   0.03505   0.02386  -0.0323   0.6649   0.7218
  -1.250   0.1085   0.03482   0.02349  -0.0322   0.6607   0.7250
  -1.000   0.1199   0.03481   0.02346  -0.0307   0.6545   0.7290
  -0.750   0.1325   0.03462   0.02320  -0.0297   0.6493   0.7333
  -0.500   0.1552   0.03447   0.02295  -0.0295   0.6453   0.7363
  -0.250   0.1744   0.03453   0.02297  -0.0287   0.6407   0.7391
   0.000   0.1878   0.03469   0.02313  -0.0274   0.6349   0.7423
   0.250   0.2078   0.03464   0.02301  -0.0270   0.6306   0.7455
   0.500   0.2313   0.03448   0.02275  -0.0273   0.6273   0.7494
   0.750   0.2403   0.03492   0.02323  -0.0256   0.6216   0.7527
   1.000   0.2568   0.03520   0.02352  -0.0247   0.6167   0.7554
   1.250   0.2803   0.03525   0.02353  -0.0247   0.6130   0.7581
   1.500   0.3077   0.03521   0.02341  -0.0251   0.6101   0.7612
   1.750   0.3077   0.03612   0.02441  -0.0230   0.6031   0.7657
   2.000   0.3265   0.03645   0.02475  -0.0226   0.5988   0.7689
   2.250   0.3520   0.03657   0.02486  -0.0226   0.5955   0.7717
   2.500   0.3632   0.03727   0.02560  -0.0214   0.5904   0.7750
   2.750   0.3695   0.03822   0.02660  -0.0200   0.5843   0.7788
   3.000   0.3936   0.03853   0.02691  -0.0205   0.5806   0.7827
   3.250   0.4226   0.03861   0.02698  -0.0209   0.5779   0.7859
   3.500   0.4086   0.04053   0.02903  -0.0176   0.5693   0.7902
   3.750   0.4281   0.04111   0.02963  -0.0174   0.5650   0.7942
   4.000   0.4593   0.04123   0.02977  -0.0184   0.5622   0.7980
   4.500   0.4594   0.04417   0.03286  -0.0148   0.5485   0.8064
   4.750   0.4911   0.04429   0.03301  -0.0155   0.5457   0.8109
   5.250   0.4913   0.04773   0.03661  -0.0128   0.5311   0.8214
   5.500   0.5247   0.04759   0.03653  -0.0132   0.5287   0.8264
   6.000   0.5316   0.05125   0.04035  -0.0119   0.5135   0.8380
   6.500   0.5447   0.05456   0.04385  -0.0109   0.4988   0.8519
   6.750   0.5771   0.05437   0.04377  -0.0109   0.4960   0.8595
   7.250   0.5917   0.05754   0.04718  -0.0100   0.4807   0.8785
   7.500   0.5822   0.06036   0.05012  -0.0093   0.4698   0.8901
   7.750   0.6111   0.06050   0.05041  -0.0095   0.4655   0.9038
   8.250   0.6440   0.06327   0.05351  -0.0115   0.4497   0.9709
   8.500   0.6454   0.06593   0.05624  -0.0126   0.4389   1.0000
   8.750   0.6768   0.06628   0.05668  -0.0137   0.4338   1.0000
   9.000   0.6778   0.06908   0.05952  -0.0146   0.4227   1.0000
   9.250   0.7098   0.06919   0.05973  -0.0153   0.4177   1.0000
   9.750   0.7425   0.07190   0.06259  -0.0164   0.4015   1.0000
  10.000   0.7385   0.07512   0.06587  -0.0171   0.3892   1.0000
  10.250   0.7748   0.07438   0.06525  -0.0171   0.3852   1.0000
  10.500   0.7697   0.07772   0.06865  -0.0177   0.3726   1.0000
  10.750   0.7702   0.08056   0.07156  -0.0182   0.3611   1.0000
  11.000   0.8020   0.07999   0.07111  -0.0180   0.3561   1.0000
  11.250   0.7990   0.08323   0.07442  -0.0186   0.3437   1.0000
  11.750   0.8303   0.08537   0.07680  -0.0186   0.3268   1.0000
  12.000   0.8285   0.08865   0.08015  -0.0193   0.3148   1.0000
  12.250   0.8565   0.08799   0.07962  -0.0187   0.3089   1.0000
  12.500   0.8590   0.09069   0.08243  -0.0193   0.2975   1.0000
  13.000   0.8930   0.09190   0.08389  -0.0188   0.2809   1.0000
  13.250   0.8871   0.09605   0.08812  -0.0199   0.2684   1.0000
  13.750   0.9220   0.09681   0.08916  -0.0193   0.2516   1.0000
  14.000   0.9155   0.10132   0.09374  -0.0207   0.2396   1.0000
  14.250   0.9625   0.09648   0.08906  -0.0182   0.2345   1.0000
  14.750   0.9451   0.10640   0.09913  -0.0215   0.2108   1.0000
  15.000   0.9843   0.10267   0.09553  -0.0194   0.2035   1.0000
  15.250   0.9847   0.10602   0.09897  -0.0205   0.1928   1.0000
  15.500   0.9706   0.11229   0.10531  -0.0229   0.1823   1.0000
  15.750   1.0031   0.10961   0.10268  -0.0212   0.1735   1.0000
  16.000   1.0041   0.11300   0.10614  -0.0224   0.1640   1.0000
  16.250   0.9846   0.12058   0.11381  -0.0258   0.1552   1.0000
  16.500   1.0230   0.11652   0.10974  -0.0234   0.1461   1.0000
  16.750   0.9833   0.12850   0.12187  -0.0291   0.1388   1.0000
  17.000   1.0049   0.12774   0.12113  -0.0284   0.1310   1.0000
  17.250   0.9729   0.13874   0.13222  -0.0340   0.1242   1.0000
  17.500   0.9900   0.13887   0.13238  -0.0339   0.1176   1.0000
  17.750   0.9467   0.15352   0.14705  -0.0417   0.1113   1.0000
  18.000   0.9841   0.14844   0.14205  -0.0388   0.1056   1.0000
  18.250   0.9243   0.16872   0.16224  -0.0500   0.0998   1.0000
  18.500   0.9628   0.16249   0.15617  -0.0466   0.0950   1.0000
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