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S4053 (s4053-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 200,000
Max Cl/Cd: 75.61 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4053-il-200000-n5.txt
Download as CSV file: xf-s4053-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3933   0.08527   0.08185  -0.0390   1.0000   0.0262
  -8.000  -0.3996   0.08203   0.07869  -0.0396   1.0000   0.0262
  -7.750  -0.4062   0.07854   0.07525  -0.0409   1.0000   0.0262
  -6.750  -0.3889   0.05365   0.05011  -0.0559   0.9880   0.0181
  -6.500  -0.3692   0.04667   0.04282  -0.0617   0.9796   0.0182
  -6.250  -0.3477   0.04078   0.03657  -0.0658   0.9713   0.0185
  -6.000  -0.3228   0.03759   0.03313  -0.0674   0.9626   0.0176
  -5.750  -0.2981   0.03289   0.02804  -0.0699   0.9553   0.0171
  -5.500  -0.2736   0.02905   0.02375  -0.0710   0.9459   0.0167
  -5.250  -0.2469   0.02584   0.02004  -0.0718   0.9372   0.0165
  -5.000  -0.2167   0.02308   0.01680  -0.0728   0.9303   0.0163
  -4.750  -0.1881   0.02094   0.01424  -0.0731   0.9213   0.0163
  -4.500  -0.1560   0.01915   0.01208  -0.0740   0.9145   0.0165
  -4.250  -0.1259   0.01774   0.01039  -0.0743   0.9053   0.0169
  -4.000  -0.0951   0.01659   0.00902  -0.0748   0.8965   0.0173
  -3.750  -0.0637   0.01571   0.00795  -0.0753   0.8879   0.0179
  -3.500  -0.0365   0.01452   0.00671  -0.0754   0.8775   0.0200
  -3.250  -0.0081   0.01388   0.00600  -0.0754   0.8675   0.0215
  -3.000   0.0201   0.01325   0.00526  -0.0754   0.8577   0.0222
  -2.750   0.0474   0.01277   0.00465  -0.0751   0.8474   0.0231
  -2.500   0.0744   0.01239   0.00413  -0.0748   0.8372   0.0245
  -2.250   0.1018   0.01208   0.00369  -0.0745   0.8277   0.0266
  -2.000   0.1288   0.01173   0.00329  -0.0742   0.8183   0.0355
  -1.750   0.1532   0.01102   0.00303  -0.0737   0.8086   0.1503
  -1.500   0.1753   0.01009   0.00293  -0.0731   0.7996   0.3797
  -1.250   0.1948   0.00930   0.00293  -0.0715   0.7908   0.6059
  -1.000   0.2148   0.00874   0.00298  -0.0690   0.7820   0.7955
  -0.750   0.2692   0.00856   0.00288  -0.0738   0.7755   0.9327
  -0.500   0.3229   0.00855   0.00275  -0.0792   0.7673   0.9887
  -0.250   0.3591   0.00858   0.00264  -0.0810   0.7591   1.0000
   0.000   0.3833   0.00865   0.00259  -0.0802   0.7499   1.0000
   0.250   0.4076   0.00872   0.00257  -0.0795   0.7410   1.0000
   0.500   0.4323   0.00881   0.00255  -0.0788   0.7327   1.0000
   0.750   0.4567   0.00889   0.00256  -0.0780   0.7230   1.0000
   1.000   0.4813   0.00898   0.00258  -0.0773   0.7136   1.0000
   1.250   0.5060   0.00908   0.00259  -0.0766   0.7043   1.0000
   1.500   0.5305   0.00917   0.00264  -0.0758   0.6938   1.0000
   1.750   0.5551   0.00927   0.00270  -0.0751   0.6835   1.0000
   2.000   0.5799   0.00938   0.00276  -0.0744   0.6734   1.0000
   2.500   0.6294   0.00960   0.00291  -0.0730   0.6508   1.0000
   2.750   0.6540   0.00971   0.00302  -0.0722   0.6380   1.0000
   3.000   0.6785   0.00983   0.00311  -0.0715   0.6244   1.0000
   3.250   0.7030   0.00996   0.00322  -0.0708   0.6101   1.0000
   3.500   0.7274   0.01010   0.00333  -0.0700   0.5946   1.0000
   3.750   0.7515   0.01025   0.00346  -0.0692   0.5768   1.0000
   4.000   0.7752   0.01042   0.00362  -0.0683   0.5550   1.0000
   4.250   0.7984   0.01062   0.00376  -0.0673   0.5297   1.0000
   4.500   0.8211   0.01086   0.00393  -0.0662   0.5008   1.0000
   4.750   0.8427   0.01118   0.00412  -0.0650   0.4671   1.0000
   5.000   0.8638   0.01156   0.00440  -0.0637   0.4289   1.0000
   5.250   0.8838   0.01202   0.00470  -0.0623   0.3875   1.0000
   5.500   0.9030   0.01258   0.00506  -0.0608   0.3429   1.0000
   5.750   0.9217   0.01319   0.00548  -0.0594   0.2983   1.0000
   6.000   0.9403   0.01385   0.00594  -0.0580   0.2548   1.0000
   6.250   0.9589   0.01452   0.00644  -0.0566   0.2157   1.0000
   6.500   0.9780   0.01517   0.00700  -0.0553   0.1827   1.0000
   6.750   0.9972   0.01581   0.00755  -0.0540   0.1556   1.0000
   7.000   1.0160   0.01647   0.00813  -0.0527   0.1313   1.0000
   7.250   1.0344   0.01718   0.00876  -0.0514   0.1096   1.0000
   7.500   1.0528   0.01787   0.00941  -0.0500   0.0929   1.0000
   7.750   1.0710   0.01856   0.01010  -0.0486   0.0808   1.0000
   8.000   1.0885   0.01929   0.01086  -0.0472   0.0710   1.0000
   8.250   1.1064   0.01997   0.01161  -0.0457   0.0630   1.0000
   8.500   1.1224   0.02077   0.01243  -0.0441   0.0563   1.0000
   8.750   1.1391   0.02149   0.01321  -0.0425   0.0500   1.0000
   9.000   1.1541   0.02230   0.01405  -0.0408   0.0442   1.0000
   9.250   1.1694   0.02301   0.01485  -0.0391   0.0390   1.0000
   9.500   1.1801   0.02396   0.01583  -0.0367   0.0349   1.0000
   9.750   1.1940   0.02471   0.01674  -0.0348   0.0311   1.0000
  10.000   1.2049   0.02568   0.01775  -0.0327   0.0272   1.0000
  10.250   1.2140   0.02680   0.01898  -0.0304   0.0244   1.0000
  10.500   1.2238   0.02790   0.02022  -0.0283   0.0218   1.0000
  10.750   1.2321   0.02914   0.02156  -0.0263   0.0198   1.0000
  11.000   1.2338   0.03095   0.02343  -0.0238   0.0180   1.0000
  11.250   1.2411   0.03240   0.02505  -0.0219   0.0168   1.0000
  11.500   1.2480   0.03390   0.02670  -0.0203   0.0154   1.0000
  11.750   1.2549   0.03542   0.02834  -0.0189   0.0141   1.0000
  12.000   1.2588   0.03727   0.03032  -0.0174   0.0134   1.0000
  12.250   1.2588   0.03955   0.03269  -0.0161   0.0125   1.0000
  12.500   1.2575   0.04215   0.03544  -0.0148   0.0121   1.0000
  12.750   1.2587   0.04463   0.03816  -0.0139   0.0117   1.0000
  13.000   1.2586   0.04732   0.04104  -0.0131   0.0114   1.0000
  13.250   1.2567   0.05033   0.04426  -0.0125   0.0109   1.0000
  13.500   1.2538   0.05354   0.04767  -0.0123   0.0107   1.0000
  13.750   1.2493   0.05707   0.05139  -0.0123   0.0104   1.0000
  14.000   1.2438   0.06084   0.05536  -0.0128   0.0101   1.0000
  14.250   1.2366   0.06498   0.05970  -0.0136   0.0099   1.0000
  14.500   1.2292   0.06932   0.06422  -0.0149   0.0096   1.0000
  14.750   1.2190   0.07433   0.06941  -0.0166   0.0094   1.0000
  15.000   1.2110   0.07920   0.07444  -0.0188   0.0092   1.0000
  15.250   1.1974   0.08541   0.08085  -0.0215   0.0091   1.0000
  15.500   1.1858   0.09157   0.08717  -0.0248   0.0090   1.0000
  15.750   1.1700   0.09893   0.09473  -0.0287   0.0090   1.0000
  16.000   1.1538   0.10683   0.10281  -0.0332   0.0090   1.0000
  16.250   1.1357   0.11558   0.11174  -0.0383   0.0090   1.0000
  16.500   1.1056   0.12795   0.12438  -0.0456   0.0093   1.0000
  16.750   1.0621   0.14528   0.14196  -0.0559   0.0101   1.0000
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