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S4158 (s4158-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 500,000
Max Cl/Cd: 124.16 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4158-il-500000.txt
Download as CSV file: xf-s4158-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4158                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2948   0.08448   0.08184  -0.0586   0.8618   0.0216
  -8.750  -0.2939   0.08041   0.07780  -0.0613   0.8597   0.0217
  -8.500  -0.2940   0.07612   0.07353  -0.0642   0.8572   0.0217
  -8.250  -0.3137   0.06927   0.06675  -0.0681   0.8539   0.0222
  -8.000  -0.3221   0.06394   0.06140  -0.0729   0.8507   0.0222
  -7.750  -0.3190   0.06079   0.05822  -0.0744   0.8486   0.0226
  -7.500  -0.3126   0.05821   0.05558  -0.0756   0.8466   0.0230
  -7.250  -0.3029   0.05542   0.05276  -0.0773   0.8445   0.0236
  -7.000  -0.2943   0.05156   0.04881  -0.0795   0.8419   0.0242
  -6.750  -0.2838   0.04770   0.04482  -0.0812   0.8394   0.0252
  -6.500  -0.2724   0.04322   0.04012  -0.0824   0.8371   0.0267
  -6.250  -0.2537   0.04040   0.03679  -0.0823   0.8350   0.0287
  -6.000  -0.2526   0.03308   0.02904  -0.0823   0.8330   0.0299
  -5.750  -0.2318   0.03114   0.02706  -0.0824   0.8311   0.0307
  -5.500  -0.2099   0.02937   0.02518  -0.0825   0.8289   0.0317
  -5.250  -0.1984   0.01855   0.01280  -0.0785   0.8262   0.0172
  -5.000  -0.1733   0.01714   0.01117  -0.0781   0.8242   0.0175
  -4.750  -0.1477   0.01612   0.01000  -0.0776   0.8223   0.0178
  -4.500  -0.1219   0.01526   0.00903  -0.0772   0.8205   0.0182
  -4.250  -0.0963   0.01452   0.00818  -0.0767   0.8189   0.0186
  -4.000  -0.0699   0.01398   0.00758  -0.0764   0.8170   0.0195
  -3.750  -0.0426   0.01355   0.00711  -0.0764   0.8143   0.0207
  -3.500  -0.0159   0.01305   0.00655  -0.0762   0.8117   0.0213
  -3.250   0.0101   0.01245   0.00589  -0.0758   0.8092   0.0222
  -3.000   0.0360   0.01189   0.00528  -0.0753   0.8071   0.0246
  -2.750   0.0629   0.01159   0.00492  -0.0750   0.8052   0.0281
  -2.500   0.0890   0.01111   0.00451  -0.0745   0.8031   0.0526
  -2.250   0.1160   0.01074   0.00437  -0.0746   0.7998   0.1021
  -2.000   0.1426   0.01038   0.00421  -0.0745   0.7967   0.1619
  -1.750   0.1681   0.00988   0.00406  -0.0743   0.7939   0.2673
  -1.500   0.1926   0.00928   0.00392  -0.0739   0.7915   0.4128
  -1.250   0.2156   0.00870   0.00384  -0.0730   0.7893   0.5731
  -1.000   0.2376   0.00821   0.00386  -0.0718   0.7851   0.7177
  -0.750   0.2603   0.00782   0.00381  -0.0703   0.7813   0.8290
  -0.500   0.3053   0.00755   0.00373  -0.0733   0.7787   0.9411
  -0.250   0.3579   0.00748   0.00358  -0.0783   0.7766   0.9761
   0.000   0.4048   0.00745   0.00345  -0.0822   0.7746   0.9928
   0.250   0.4492   0.00740   0.00339  -0.0860   0.7707   1.0000
   0.500   0.4744   0.00737   0.00332  -0.0855   0.7665   1.0000
   0.750   0.4998   0.00732   0.00321  -0.0849   0.7632   1.0000
   1.000   0.5254   0.00727   0.00309  -0.0844   0.7603   1.0000
   1.250   0.5513   0.00728   0.00311  -0.0841   0.7550   1.0000
   1.500   0.5773   0.00723   0.00303  -0.0837   0.7505   1.0000
   1.750   0.6035   0.00716   0.00292  -0.0832   0.7468   1.0000
   2.000   0.6296   0.00715   0.00292  -0.0829   0.7408   1.0000
   2.250   0.6558   0.00707   0.00281  -0.0825   0.7349   1.0000
   2.500   0.6820   0.00699   0.00273  -0.0821   0.7273   1.0000
   2.750   0.7083   0.00690   0.00262  -0.0816   0.7192   1.0000
   3.000   0.7345   0.00688   0.00261  -0.0813   0.7097   1.0000
   3.250   0.7608   0.00686   0.00258  -0.0810   0.7006   1.0000
   3.500   0.7870   0.00686   0.00254  -0.0806   0.6904   1.0000
   3.750   0.8131   0.00689   0.00258  -0.0802   0.6778   1.0000
   4.000   0.8388   0.00695   0.00261  -0.0798   0.6638   1.0000
   4.250   0.8641   0.00705   0.00265  -0.0793   0.6484   1.0000
   4.500   0.8892   0.00718   0.00277  -0.0788   0.6311   1.0000
   4.750   0.9138   0.00736   0.00289  -0.0782   0.6115   1.0000
   5.000   0.9372   0.00762   0.00304  -0.0774   0.5852   1.0000
   5.250   0.9593   0.00795   0.00324  -0.0765   0.5528   1.0000
   5.500   0.9809   0.00832   0.00349  -0.0755   0.5213   1.0000
   5.750   1.0013   0.00875   0.00379  -0.0743   0.4867   1.0000
   6.000   1.0212   0.00920   0.00411  -0.0731   0.4537   1.0000
   6.250   1.0404   0.00968   0.00446  -0.0718   0.4214   1.0000
   6.500   1.0582   0.01022   0.00485  -0.0703   0.3879   1.0000
   6.750   1.0757   0.01076   0.00526  -0.0687   0.3539   1.0000
   7.000   1.0913   0.01137   0.00571  -0.0669   0.3178   1.0000
   7.250   1.1050   0.01205   0.00620  -0.0649   0.2780   1.0000
   7.500   1.1173   0.01277   0.00674  -0.0626   0.2426   1.0000
   7.750   1.1283   0.01346   0.00728  -0.0600   0.2120   1.0000
   8.000   1.1367   0.01416   0.00787  -0.0571   0.1862   1.0000
   8.250   1.1465   0.01491   0.00849  -0.0546   0.1615   1.0000
   8.500   1.1576   0.01566   0.00915  -0.0524   0.1373   1.0000
   8.750   1.1679   0.01653   0.00988  -0.0502   0.1122   1.0000
   9.000   1.1776   0.01748   0.01069  -0.0480   0.0889   1.0000
   9.250   1.1877   0.01844   0.01155  -0.0459   0.0721   1.0000
   9.750   1.2114   0.02022   0.01330  -0.0424   0.0535   1.0000
  10.000   1.2212   0.02128   0.01432  -0.0404   0.0466   1.0000
  10.250   1.2356   0.02203   0.01514  -0.0391   0.0432   1.0000
  10.500   1.2473   0.02300   0.01612  -0.0375   0.0393   1.0000
  10.750   1.2553   0.02424   0.01741  -0.0356   0.0356   1.0000
  11.000   1.2691   0.02508   0.01832  -0.0343   0.0333   1.0000
  11.250   1.2803   0.02613   0.01941  -0.0329   0.0306   1.0000
  11.500   1.2819   0.02792   0.02124  -0.0306   0.0276   1.0000
  11.750   1.2964   0.02876   0.02217  -0.0296   0.0261   1.0000
  12.000   1.3072   0.02989   0.02336  -0.0283   0.0242   1.0000
  12.250   1.3158   0.03122   0.02472  -0.0269   0.0225   1.0000
  12.500   1.3127   0.03355   0.02713  -0.0247   0.0209   1.0000
  12.750   1.3218   0.03491   0.02860  -0.0235   0.0199   1.0000
  13.000   1.3304   0.03634   0.03012  -0.0224   0.0188   1.0000
  13.250   1.3375   0.03793   0.03178  -0.0213   0.0177   1.0000
  13.500   1.3428   0.03973   0.03365  -0.0202   0.0166   1.0000
  13.750   1.3416   0.04222   0.03621  -0.0190   0.0156   1.0000
  14.000   1.3391   0.04499   0.03910  -0.0177   0.0150   1.0000
  14.250   1.3455   0.04689   0.04112  -0.0171   0.0145   1.0000
  14.500   1.3499   0.04909   0.04343  -0.0165   0.0141   1.0000
  14.750   1.3523   0.05156   0.04602  -0.0160   0.0135   1.0000
  15.000   1.3549   0.05410   0.04866  -0.0156   0.0131   1.0000
  15.250   1.3569   0.05676   0.05141  -0.0155   0.0126   1.0000
  15.500   1.3573   0.05969   0.05444  -0.0155   0.0122   1.0000
  15.750   1.3564   0.06288   0.05770  -0.0157   0.0117   1.0000
  16.000   1.3486   0.06701   0.06194  -0.0159   0.0112   1.0000
  16.250   1.3409   0.07129   0.06637  -0.0163   0.0109   1.0000
  16.500   1.3382   0.07508   0.07031  -0.0170   0.0108   1.0000
  16.750   1.3363   0.07893   0.07433  -0.0180   0.0105   1.0000
  17.000   1.3320   0.08315   0.07870  -0.0192   0.0104   1.0000
  17.250   1.3270   0.08763   0.08332  -0.0207   0.0102   1.0000
  17.500   1.3212   0.09237   0.08821  -0.0225   0.0099   1.0000
  17.750   1.3119   0.09779   0.09379  -0.0244   0.0099   1.0000
  18.000   1.3036   0.10322   0.09936  -0.0268   0.0097   1.0000
  18.250   1.2943   0.10896   0.10526  -0.0295   0.0095   1.0000
  18.500   1.2842   0.11501   0.11145  -0.0324   0.0094   1.0000
  18.750   1.2716   0.12167   0.11827  -0.0358   0.0094   1.0000
  19.000   1.2613   0.12811   0.12485  -0.0393   0.0092   1.0000
  19.250   1.2478   0.13533   0.13222  -0.0434   0.0092   1.0000
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