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S4110 (s4110-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 200,000
Max Cl/Cd: 81.44 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4110-il-200000.txt
Download as CSV file: xf-s4110-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4047   0.09123   0.08781  -0.0375   1.0000   0.0497
  -8.000  -0.4121   0.08831   0.08497  -0.0386   1.0000   0.0498
  -7.750  -0.4195   0.08308   0.07981  -0.0389   1.0000   0.0503
  -7.500  -0.4160   0.08035   0.07711  -0.0349   1.0000   0.0511
  -7.250  -0.4162   0.07803   0.07484  -0.0332   1.0000   0.0517
  -7.000  -0.4184   0.07582   0.07267  -0.0318   1.0000   0.0525
  -6.750  -0.4228   0.07344   0.07033  -0.0310   1.0000   0.0532
  -6.500  -0.4272   0.07087   0.06779  -0.0308   1.0000   0.0540
  -6.250  -0.4299   0.06795   0.06489  -0.0313   1.0000   0.0548
  -6.000  -0.4298   0.06463   0.06157  -0.0327   1.0000   0.0562
  -5.750  -0.4252   0.06049   0.05736  -0.0355   1.0000   0.0584
  -5.500  -0.3873   0.04944   0.04573  -0.0512   0.9956   0.0635
  -5.250  -0.3524   0.03474   0.03013  -0.0587   0.9924   0.0375
  -5.000  -0.3189   0.02853   0.02330  -0.0627   0.9888   0.0350
  -4.750  -0.2819   0.02454   0.01862  -0.0656   0.9858   0.0355
  -4.500  -0.2428   0.02208   0.01560  -0.0681   0.9833   0.0372
  -4.250  -0.2097   0.02003   0.01311  -0.0692   0.9786   0.0379
  -4.000  -0.1739   0.01795   0.01071  -0.0708   0.9751   0.0401
  -3.750  -0.1354   0.01693   0.00963  -0.0730   0.9719   0.0455
  -3.500  -0.1005   0.01603   0.00869  -0.0745   0.9672   0.0563
  -3.250  -0.0648   0.01545   0.00802  -0.0760   0.9619   0.0761
  -3.000  -0.0254   0.01498   0.00760  -0.0786   0.9583   0.0950
  -2.750   0.0087   0.01463   0.00727  -0.0800   0.9526   0.1115
  -2.500   0.0449   0.01412   0.00679  -0.0816   0.9473   0.1277
  -2.250   0.0857   0.01352   0.00629  -0.0843   0.9440   0.1524
  -2.000   0.1190   0.01296   0.00596  -0.0855   0.9378   0.2004
  -1.750   0.1558   0.01207   0.00573  -0.0877   0.9329   0.3553
  -1.500   0.1941   0.01120   0.00563  -0.0898   0.9297   0.5727
  -1.250   0.2192   0.01067   0.00563  -0.0885   0.9220   0.7282
  -1.000   0.2537   0.01011   0.00547  -0.0884   0.9177   0.9189
  -0.750   0.3077   0.00984   0.00507  -0.0934   0.9148   1.0000
  -0.500   0.3372   0.00978   0.00491  -0.0934   0.9052   1.0000
  -0.250   0.3749   0.00960   0.00461  -0.0949   0.8995   1.0000
   0.000   0.4021   0.00956   0.00449  -0.0944   0.8884   1.0000
   0.250   0.4310   0.00951   0.00436  -0.0942   0.8783   1.0000
   0.500   0.4617   0.00941   0.00418  -0.0942   0.8691   1.0000
   0.750   0.4892   0.00937   0.00406  -0.0937   0.8574   1.0000
   1.000   0.5157   0.00935   0.00398  -0.0929   0.8446   1.0000
   1.250   0.5424   0.00934   0.00392  -0.0922   0.8318   1.0000
   1.500   0.5691   0.00934   0.00387  -0.0915   0.8184   1.0000
   1.750   0.5957   0.00935   0.00382  -0.0908   0.8042   1.0000
   2.000   0.6221   0.00936   0.00378  -0.0901   0.7889   1.0000
   2.250   0.6483   0.00939   0.00375  -0.0893   0.7727   1.0000
   2.500   0.6747   0.00943   0.00374  -0.0885   0.7556   1.0000
   2.750   0.7003   0.00949   0.00376  -0.0877   0.7361   1.0000
   3.000   0.7259   0.00957   0.00378  -0.0868   0.7149   1.0000
   3.250   0.7513   0.00967   0.00381  -0.0860   0.6920   1.0000
   3.500   0.7766   0.00980   0.00388  -0.0851   0.6677   1.0000
   3.750   0.8013   0.00997   0.00397  -0.0842   0.6401   1.0000
   4.000   0.8256   0.01018   0.00408  -0.0832   0.6098   1.0000
   4.250   0.8494   0.01043   0.00423  -0.0822   0.5748   1.0000
   4.500   0.8724   0.01077   0.00443  -0.0810   0.5369   1.0000
   4.750   0.8947   0.01117   0.00466  -0.0798   0.4942   1.0000
   5.000   0.9163   0.01165   0.00495  -0.0786   0.4485   1.0000
   5.250   0.9373   0.01220   0.00529  -0.0773   0.4015   1.0000
   5.500   0.9578   0.01282   0.00571  -0.0760   0.3551   1.0000
   5.750   0.9782   0.01349   0.00617  -0.0748   0.3122   1.0000
   6.000   0.9986   0.01419   0.00668  -0.0736   0.2739   1.0000
   6.250   1.0193   0.01489   0.00722  -0.0725   0.2403   1.0000
   6.500   1.0400   0.01560   0.00780  -0.0715   0.2128   1.0000
   6.750   1.0604   0.01635   0.00843  -0.0704   0.1906   1.0000
   7.000   1.0818   0.01702   0.00907  -0.0694   0.1709   1.0000
   7.250   1.1026   0.01773   0.00973  -0.0684   0.1542   1.0000
   7.500   1.1231   0.01848   0.01044  -0.0673   0.1398   1.0000
   7.750   1.1434   0.01924   0.01121  -0.0662   0.1264   1.0000
   8.000   1.1632   0.02004   0.01201  -0.0650   0.1140   1.0000
   8.250   1.1823   0.02093   0.01290  -0.0638   0.1029   1.0000
   8.500   1.2006   0.02191   0.01386  -0.0624   0.0929   1.0000
   8.750   1.2185   0.02286   0.01480  -0.0611   0.0838   1.0000
   9.000   1.2373   0.02377   0.01583  -0.0598   0.0760   1.0000
   9.250   1.2535   0.02505   0.01710  -0.0583   0.0692   1.0000
   9.500   1.2715   0.02583   0.01802  -0.0569   0.0629   1.0000
   9.750   1.2865   0.02734   0.01952  -0.0553   0.0575   1.0000
  10.000   1.3027   0.02822   0.02057  -0.0537   0.0526   1.0000
  10.250   1.3159   0.02974   0.02205  -0.0521   0.0482   1.0000
  10.500   1.3291   0.03107   0.02360  -0.0501   0.0446   1.0000
  10.750   1.3402   0.03222   0.02490  -0.0480   0.0413   1.0000
  11.000   1.3509   0.03403   0.02672  -0.0462   0.0385   1.0000
  11.250   1.3619   0.03646   0.02939  -0.0443   0.0363   1.0000
  11.500   1.3690   0.03806   0.03122  -0.0420   0.0342   1.0000
  11.750   1.3741   0.03963   0.03294  -0.0397   0.0323   1.0000
  12.000   1.3789   0.04124   0.03462  -0.0377   0.0306   1.0000
  12.250   1.3822   0.04486   0.03838  -0.0361   0.0290   1.0000
  12.500   1.3780   0.04803   0.04187  -0.0339   0.0284   1.0000
  12.750   1.3729   0.05080   0.04493  -0.0319   0.0279   1.0000
  13.000   1.3649   0.05406   0.04849  -0.0303   0.0273   1.0000
  13.250   1.3542   0.05783   0.05254  -0.0293   0.0269   1.0000
  13.500   1.3407   0.06212   0.05710  -0.0289   0.0267   1.0000
  13.750   1.3249   0.06692   0.06217  -0.0292   0.0264   1.0000
  14.000   1.3063   0.07246   0.06797  -0.0305   0.0263   1.0000
  14.250   1.2855   0.07875   0.07450  -0.0329   0.0263   1.0000
  14.500   1.2620   0.08606   0.08205  -0.0364   0.0264   1.0000
  14.750   1.2363   0.09447   0.09069  -0.0413   0.0267   1.0000
  15.000   1.2085   0.10423   0.10066  -0.0475   0.0271   1.0000
  15.250   1.1784   0.11556   0.11217  -0.0552   0.0276   1.0000
  15.500   1.1450   0.12888   0.12563  -0.0642   0.0282   1.0000
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