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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 100,000
Max Cl/Cd: 48.31 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e431-il-100000.txt
Download as CSV file: xf-e431-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 431 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2822   0.11346   0.10915  -0.0614   0.9730   0.0894
  -9.000  -0.3047   0.11046   0.10623  -0.0688   0.9649   0.0919
  -8.750  -0.2981   0.10519   0.10099  -0.0722   0.9609   0.0935
  -8.500  -0.2621   0.10184   0.09759  -0.0706   0.9595   0.0978
  -8.250  -0.2639   0.09917   0.09494  -0.0713   0.9525   0.1010
  -8.000  -0.2806   0.09508   0.09090  -0.0789   0.9460   0.1055
  -7.750  -0.3132   0.09290   0.08876  -0.0797   0.9360   0.1059
  -7.500  -0.3517   0.09037   0.08609  -0.0828   0.9259   0.1066
  -7.250  -0.3136   0.08577   0.08167  -0.0803   0.9253   0.1101
  -7.000  -0.3081   0.08334   0.07925  -0.0795   0.9200   0.1144
  -6.750  -0.3188   0.07958   0.07536  -0.0833   0.9136   0.1195
  -6.500  -0.3643   0.07835   0.07376  -0.0824   0.9030   0.1225
  -6.250  -0.3288   0.07386   0.06960  -0.0812   0.9017   0.1277
  -6.000  -0.3336   0.07175   0.06737  -0.0804   0.8956   0.1341
  -5.750  -0.3436   0.06889   0.06435  -0.0797   0.8891   0.1404
  -5.250  -0.3156   0.06391   0.05924  -0.0801   0.8815   0.1659
  -5.000  -0.3204   0.06195   0.05726  -0.0773   0.8751   0.1752
  -4.750  -0.2789   0.04957   0.04245  -0.0814   0.8719   0.0673
  -4.500  -0.2478   0.04553   0.03836  -0.0832   0.8694   0.0625
  -4.250  -0.2044   0.04168   0.03357  -0.0851   0.8673   0.0549
  -4.000  -0.2026   0.04078   0.03247  -0.0813   0.8608   0.0542
  -3.750  -0.1748   0.03908   0.03044  -0.0813   0.8569   0.0535
  -3.500  -0.1388   0.03742   0.02840  -0.0822   0.8538   0.0548
  -3.250  -0.0975   0.03599   0.02688  -0.0844   0.8514   0.0609
  -3.000  -0.0972   0.03604   0.02686  -0.0803   0.8443   0.0650
  -2.750  -0.0708   0.03504   0.02594  -0.0801   0.8403   0.0723
  -2.500  -0.0358   0.03394   0.02499  -0.0813   0.8372   0.0980
  -2.250  -0.0107   0.03286   0.02435  -0.0813   0.8330   0.1647
  -2.000  -0.0197   0.03104   0.02529  -0.0746   0.8274   0.6863
  -1.750  -0.0182   0.03221   0.02646  -0.0668   0.8225   0.7979
  -1.500  -0.0103   0.03289   0.02703  -0.0596   0.8190   0.8470
  -1.250  -0.0271   0.03349   0.02764  -0.0522   0.8109   0.8661
  -1.000  -0.0244   0.03369   0.02773  -0.0457   0.8061   0.8997
  -0.750   0.0027   0.03385   0.02772  -0.0428   0.8029   0.9401
  -0.500   0.2885   0.03511   0.02814  -0.0887   0.8051   1.0000
  -0.250   0.2714   0.03588   0.02889  -0.0826   0.7966   1.0000
   0.000   0.2840   0.03610   0.02901  -0.0810   0.7906   1.0000
   0.250   0.3216   0.03600   0.02876  -0.0830   0.7874   1.0000
   0.500   0.2842   0.03696   0.02975  -0.0740   0.7763   1.0000
   0.750   0.3161   0.03692   0.02958  -0.0749   0.7722   1.0000
   1.000   0.2872   0.03771   0.03037  -0.0673   0.7620   1.0000
   1.250   0.3108   0.03775   0.03032  -0.0670   0.7571   1.0000
   1.500   0.2941   0.03834   0.03089  -0.0611   0.7480   1.0000
   1.750   0.3115   0.03844   0.03091  -0.0599   0.7418   1.0000
   2.000   0.3533   0.03834   0.03071  -0.0620   0.7387   1.0000
   2.250   0.3359   0.03931   0.03167  -0.0570   0.7269   1.0000
   2.500   0.3786   0.03930   0.03156  -0.0593   0.7234   1.0000
   2.750   0.3789   0.04043   0.03267  -0.0571   0.7124   1.0000
   3.000   0.4210   0.04040   0.03258  -0.0594   0.7083   1.0000
   3.250   0.4295   0.04153   0.03369  -0.0583   0.6978   1.0000
   3.500   0.4695   0.04153   0.03364  -0.0603   0.6931   1.0000
   3.750   0.5185   0.04118   0.03326  -0.0630   0.6905   1.0000
   4.000   0.5212   0.04259   0.03469  -0.0615   0.6778   1.0000
   4.250   0.5699   0.04210   0.03417  -0.0640   0.6752   1.0000
   4.500   0.5750   0.04354   0.03562  -0.0628   0.6625   1.0000
   4.750   0.6227   0.04296   0.03504  -0.0651   0.6598   1.0000
   5.000   0.6298   0.04435   0.03647  -0.0640   0.6472   1.0000
   5.250   0.6778   0.04357   0.03571  -0.0661   0.6445   1.0000
   5.500   0.6856   0.04497   0.03713  -0.0650   0.6318   1.0000
   5.750   0.7343   0.04395   0.03614  -0.0670   0.6292   1.0000
   6.000   0.7428   0.04532   0.03757  -0.0659   0.6164   1.0000
   6.250   0.7917   0.04405   0.03636  -0.0677   0.6139   1.0000
   6.500   0.8012   0.04536   0.03770  -0.0666   0.6012   1.0000
   6.750   0.8507   0.04379   0.03623  -0.0682   0.5987   1.0000
   7.000   0.9055   0.04163   0.03417  -0.0700   0.5975   1.0000
   7.500   0.9252   0.04389   0.03657  -0.0674   0.5715   1.0000
   7.750   0.9798   0.04121   0.03401  -0.0687   0.5698   1.0000
   8.000   1.0410   0.03798   0.03093  -0.0705   0.5688   1.0000
   8.250   1.0823   0.03645   0.02951  -0.0711   0.5622   1.0000
   8.500   1.1310   0.03437   0.02758  -0.0724   0.5552   1.0000
   8.750   1.2287   0.02977   0.02315  -0.0791   0.5514   1.0000
   9.000   1.2511   0.02947   0.02293  -0.0780   0.5373   1.0000
   9.250   1.2809   0.02882   0.02236  -0.0777   0.5225   1.0000
   9.500   1.3148   0.02805   0.02164  -0.0779   0.5059   1.0000
   9.750   1.3406   0.02775   0.02135  -0.0772   0.4877   1.0000
  10.000   1.3480   0.02830   0.02195  -0.0744   0.4687   1.0000
  10.250   1.3605   0.02870   0.02236  -0.0723   0.4483   1.0000
  10.500   1.3814   0.02885   0.02240  -0.0711   0.4266   1.0000
  10.750   1.3820   0.02996   0.02354  -0.0679   0.4059   1.0000
  11.000   1.3875   0.03095   0.02449  -0.0653   0.3845   1.0000
  11.250   1.3955   0.03194   0.02537  -0.0632   0.3630   1.0000
  11.500   1.3947   0.03345   0.02690  -0.0603   0.3426   1.0000
  11.750   1.3963   0.03494   0.02833  -0.0579   0.3223   1.0000
  12.000   1.4006   0.03638   0.02963  -0.0558   0.3024   1.0000
  12.250   1.3979   0.03830   0.03156  -0.0534   0.2836   1.0000
  12.500   1.3959   0.04028   0.03353  -0.0512   0.2652   1.0000
  12.750   1.3944   0.04234   0.03556  -0.0493   0.2474   1.0000
  13.000   1.3931   0.04447   0.03766  -0.0475   0.2305   1.0000
  13.250   1.3916   0.04672   0.03987  -0.0458   0.2143   1.0000
  13.500   1.3900   0.04909   0.04219  -0.0444   0.1987   1.0000
  13.750   1.3880   0.05159   0.04466  -0.0430   0.1840   1.0000
  14.000   1.3857   0.05424   0.04730  -0.0419   0.1700   1.0000
  14.250   1.3835   0.05699   0.05007  -0.0409   0.1568   1.0000
  14.500   1.3816   0.05983   0.05293  -0.0400   0.1444   1.0000
  14.750   1.3805   0.06272   0.05583  -0.0392   0.1330   1.0000
  15.000   1.3808   0.06555   0.05865  -0.0386   0.1225   1.0000
  15.250   1.3842   0.06813   0.06114  -0.0381   0.1123   1.0000
  15.500   1.3803   0.07154   0.06474  -0.0378   0.1042   1.0000
  15.750   1.3820   0.07452   0.06778  -0.0374   0.0962   1.0000
  16.000   1.3918   0.07667   0.06976  -0.0370   0.0878   1.0000
  16.250   1.3836   0.08082   0.07425  -0.0371   0.0829   1.0000
  16.500   1.3950   0.08289   0.07618  -0.0368   0.0760   1.0000
  16.750   1.3857   0.08732   0.08096  -0.0372   0.0723   1.0000
  17.000   1.4010   0.08904   0.08249  -0.0369   0.0659   1.0000
  17.250   1.3881   0.09401   0.08785  -0.0377   0.0637   1.0000
  17.500   1.3790   0.09865   0.09276  -0.0387   0.0609   1.0000
  17.750   1.3941   0.10040   0.09433  -0.0385   0.0560   1.0000
  18.000   1.3770   0.10618   0.10049  -0.0402   0.0548   1.0000
  18.250   1.3612   0.11208   0.10670  -0.0422   0.0534   1.0000
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