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EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 625 AIRFOIL (e625-il)
Reynolds number: 500,000
Max Cl/Cd: 76.55 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e625-il-500000-n5.txt
Download as CSV file: xf-e625-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 625 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4827   0.08250   0.08024  -0.0242   1.0000   0.0119
 -10.000  -0.5102   0.07282   0.07057  -0.0324   1.0000   0.0117
  -9.750  -0.5504   0.06419   0.06186  -0.0361   1.0000   0.0116
  -9.500  -0.5886   0.05786   0.05540  -0.0339   1.0000   0.0116
  -9.250  -0.6913   0.04040   0.03723  -0.0233   1.0000   0.0116
  -9.000  -0.7012   0.02978   0.02551  -0.0225   0.9361   0.0117
  -8.750  -0.6768   0.02701   0.02226  -0.0234   0.8947   0.0119
  -8.500  -0.6629   0.02532   0.02018  -0.0212   0.8612   0.0121
  -8.250  -0.6483   0.02395   0.01848  -0.0189   0.8370   0.0124
  -8.000  -0.6321   0.02271   0.01691  -0.0168   0.8157   0.0127
  -7.750  -0.6141   0.02155   0.01547  -0.0150   0.7975   0.0129
  -7.500  -0.5944   0.02052   0.01417  -0.0134   0.7805   0.0130
  -7.250  -0.5733   0.01967   0.01309  -0.0121   0.7646   0.0132
  -7.000  -0.5512   0.01891   0.01213  -0.0109   0.7494   0.0133
  -6.750  -0.5287   0.01798   0.01104  -0.0099   0.7357   0.0134
  -6.500  -0.5058   0.01717   0.01012  -0.0089   0.7215   0.0137
  -6.250  -0.4824   0.01662   0.00948  -0.0080   0.7081   0.0139
  -6.000  -0.4587   0.01609   0.00884  -0.0072   0.6946   0.0141
  -5.750  -0.4346   0.01561   0.00828  -0.0063   0.6811   0.0144
  -5.500  -0.4105   0.01514   0.00772  -0.0055   0.6683   0.0146
  -5.250  -0.3864   0.01473   0.00722  -0.0047   0.6562   0.0150
  -5.000  -0.3624   0.01433   0.00673  -0.0038   0.6436   0.0153
  -4.750  -0.3382   0.01394   0.00626  -0.0029   0.6315   0.0156
  -4.500  -0.3138   0.01361   0.00586  -0.0021   0.6198   0.0161
  -4.250  -0.2896   0.01332   0.00549  -0.0013   0.6082   0.0163
  -4.000  -0.2661   0.01295   0.00506  -0.0003   0.5957   0.0169
  -3.750  -0.2422   0.01263   0.00471   0.0006   0.5839   0.0175
  -3.500  -0.2180   0.01238   0.00441   0.0015   0.5721   0.0180
  -3.250  -0.1937   0.01217   0.00413   0.0023   0.5607   0.0185
  -3.000  -0.1692   0.01196   0.00386   0.0031   0.5494   0.0192
  -2.750  -0.1445   0.01179   0.00363   0.0039   0.5387   0.0200
  -2.500  -0.1202   0.01160   0.00339   0.0047   0.5280   0.0210
  -2.250  -0.0954   0.01144   0.00320   0.0055   0.5172   0.0224
  -1.500  -0.0226   0.01095   0.00272   0.0080   0.4861   0.0504
  -1.250   0.0009   0.01076   0.00261   0.0089   0.4769   0.0818
  -1.000   0.0248   0.01061   0.00252   0.0098   0.4668   0.1108
  -0.750   0.0480   0.01041   0.00245   0.0108   0.4568   0.1549
  -0.500   0.0685   0.01008   0.00237   0.0121   0.4475   0.2390
  -0.250   0.0648   0.00860   0.00209   0.0182   0.4406   0.5821
   0.000   0.0698   0.00780   0.00227   0.0236   0.4331   0.8409
   0.250   0.0962   0.00795   0.00243   0.0244   0.4231   0.8769
   0.500   0.1250   0.00815   0.00258   0.0246   0.4132   0.8949
   0.750   0.1534   0.00832   0.00269   0.0247   0.4036   0.9044
   1.000   0.1821   0.00849   0.00280   0.0248   0.3943   0.9120
   1.250   0.2130   0.00873   0.00295   0.0244   0.3841   0.9191
   1.500   0.2437   0.00898   0.00315   0.0242   0.3752   0.9272
   1.750   0.2793   0.00920   0.00330   0.0227   0.3661   0.9301
   2.000   0.3076   0.00930   0.00333   0.0226   0.3570   0.9318
   2.250   0.3344   0.00940   0.00336   0.0228   0.3486   0.9340
   2.500   0.3577   0.00947   0.00338   0.0238   0.3409   0.9369
   2.750   0.3765   0.00951   0.00338   0.0256   0.3343   0.9404
   3.000   0.4071   0.00963   0.00344   0.0250   0.3259   0.9413
   3.250   0.4377   0.00976   0.00352   0.0243   0.3183   0.9422
   3.500   0.4680   0.00990   0.00361   0.0237   0.3102   0.9432
   3.750   0.4976   0.01004   0.00371   0.0232   0.3034   0.9443
   4.000   0.5267   0.01017   0.00380   0.0229   0.2961   0.9455
   4.250   0.5549   0.01032   0.00391   0.0227   0.2896   0.9470
   4.500   0.5827   0.01044   0.00401   0.0225   0.2829   0.9486
   4.750   0.6083   0.01059   0.00412   0.0229   0.2766   0.9508
   5.000   0.6238   0.01067   0.00420   0.0254   0.2723   0.9555
   5.250   0.6546   0.01083   0.00433   0.0246   0.2656   0.9562
   5.500   0.6850   0.01102   0.00450   0.0238   0.2596   0.9570
   5.750   0.7158   0.01117   0.00465   0.0230   0.2542   0.9577
   6.000   0.7458   0.01136   0.00481   0.0223   0.2483   0.9585
   6.250   0.7756   0.01155   0.00501   0.0216   0.2430   0.9595
   6.500   0.8053   0.01173   0.00519   0.0209   0.2372   0.9607
   6.750   0.8336   0.01196   0.00539   0.0205   0.2320   0.9621
   7.000   0.8610   0.01214   0.00560   0.0203   0.2270   0.9637
   7.250   0.8864   0.01234   0.00579   0.0205   0.2214   0.9658
   7.500   0.9029   0.01254   0.00598   0.0226   0.2169   0.9699
   7.750   0.9335   0.01275   0.00623   0.0217   0.2122   0.9706
   8.000   0.9634   0.01299   0.00647   0.0208   0.2064   0.9715
   8.250   0.9922   0.01329   0.00676   0.0201   0.2008   0.9725
   8.500   1.0211   0.01352   0.00702   0.0195   0.1961   0.9737
   8.750   1.0485   0.01379   0.00731   0.0191   0.1908   0.9751
   9.000   1.0746   0.01411   0.00763   0.0189   0.1857   0.9768
   9.250   1.1000   0.01437   0.00793   0.0189   0.1808   0.9788
   9.500   1.1222   0.01469   0.00826   0.0195   0.1760   0.9816
   9.750   1.1471   0.01504   0.00863   0.0195   0.1714   0.9835
  10.000   1.1754   0.01536   0.00899   0.0188   0.1662   0.9847
  10.250   1.2018   0.01578   0.00942   0.0183   0.1610   0.9862
  10.500   1.2278   0.01616   0.00984   0.0179   0.1565   0.9879
  10.750   1.2526   0.01656   0.01028   0.0177   0.1514   0.9899
  11.000   1.2748   0.01707   0.01080   0.0179   0.1467   0.9923
  11.250   1.2987   0.01750   0.01129   0.0178   0.1426   0.9944
  11.500   1.3239   0.01799   0.01182   0.0173   0.1375   0.9964
  11.750   1.3457   0.01859   0.01243   0.0172   0.1324   0.9987
  12.000   1.3612   0.01906   0.01295   0.0185   0.1273   1.0000
  12.250   1.3546   0.01951   0.01343   0.0240   0.1245   1.0000
  12.500   1.3495   0.02017   0.01411   0.0287   0.1211   1.0000
  12.750   1.3510   0.02086   0.01484   0.0320   0.1177   1.0000
  13.000   1.3524   0.02175   0.01576   0.0348   0.1121   1.0000
  13.250   1.3533   0.02288   0.01690   0.0373   0.1084   1.0000
  13.500   1.3589   0.02391   0.01799   0.0391   0.1048   1.0000
  13.750   1.3625   0.02520   0.01932   0.0407   0.1003   1.0000
  14.000   1.3645   0.02676   0.02091   0.0420   0.0969   1.0000
  14.250   1.3695   0.02821   0.02243   0.0430   0.0940   1.0000
  14.500   1.3734   0.02987   0.02415   0.0437   0.0907   1.0000
  14.750   1.3736   0.03194   0.02626   0.0443   0.0868   1.0000
  15.000   1.3742   0.03407   0.02845   0.0447   0.0835   1.0000
  15.250   1.3757   0.03621   0.03067   0.0450   0.0809   1.0000
  15.500   1.3724   0.03891   0.03341   0.0450   0.0770   1.0000
  15.750   1.3673   0.04188   0.03644   0.0448   0.0737   1.0000
  16.000   1.3618   0.04498   0.03960   0.0445   0.0689   1.0000
  16.250   1.3597   0.04779   0.04251   0.0442   0.0683   1.0000
  16.500   1.3462   0.05202   0.04677   0.0433   0.0635   1.0000
  16.750   1.3393   0.05560   0.05044   0.0425   0.0608   1.0000
  17.000   1.3323   0.05931   0.05423   0.0415   0.0592   1.0000
  17.250   1.3182   0.06400   0.05898   0.0401   0.0563   1.0000
  17.500   1.3083   0.06823   0.06331   0.0388   0.0547   1.0000
  17.750   1.2946   0.07311   0.06825   0.0372   0.0511   1.0000
  18.000   1.2824   0.07783   0.07306   0.0356   0.0493   1.0000
  18.250   1.2647   0.08344   0.07873   0.0336   0.0465   1.0000
  18.500   1.2559   0.08788   0.08326   0.0320   0.0457   1.0000
  18.750   1.2426   0.09301   0.08847   0.0301   0.0434   1.0000
  19.000   1.2311   0.09794   0.09349   0.0281   0.0424   1.0000
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