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S4110 (s4110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.65 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4110-il-1000000.txt
Download as CSV file: xf-s4110-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4084   0.08226   0.08067  -0.0324   1.0000   0.0140
  -8.250  -0.4158   0.07888   0.07733  -0.0325   1.0000   0.0140
  -8.000  -0.4236   0.07686   0.07534  -0.0312   1.0000   0.0146
  -7.750  -0.4534   0.03211   0.02993  -0.0810   0.9876   0.0132
  -7.500  -0.4331   0.01837   0.01474  -0.0895   0.9838   0.0102
  -7.250  -0.4052   0.01659   0.01270  -0.0904   0.9801   0.0103
  -7.000  -0.3743   0.01524   0.01116  -0.0916   0.9772   0.0105
  -6.750  -0.3423   0.01394   0.00965  -0.0930   0.9748   0.0107
  -6.500  -0.3101   0.01271   0.00823  -0.0942   0.9724   0.0108
  -6.250  -0.2794   0.01176   0.00714  -0.0949   0.9691   0.0110
  -6.000  -0.2523   0.01104   0.00631  -0.0948   0.9627   0.0113
  -5.750  -0.2221   0.01044   0.00562  -0.0953   0.9581   0.0118
  -5.500  -0.1946   0.00996   0.00505  -0.0951   0.9512   0.0122
  -5.250  -0.1661   0.00957   0.00459  -0.0952   0.9445   0.0124
  -5.000  -0.1395   0.00883   0.00373  -0.0949   0.9364   0.0131
  -4.750  -0.1117   0.00842   0.00323  -0.0947   0.9290   0.0139
  -4.500  -0.0847   0.00812   0.00288  -0.0945   0.9201   0.0147
  -4.250  -0.0571   0.00787   0.00257  -0.0942   0.9122   0.0157
  -4.000  -0.0299   0.00763   0.00227  -0.0939   0.9033   0.0180
  -3.750  -0.0027   0.00727   0.00199  -0.0937   0.8948   0.0337
  -3.500   0.0247   0.00712   0.00185  -0.0934   0.8862   0.0466
  -3.250   0.0523   0.00702   0.00172  -0.0932   0.8773   0.0527
  -3.000   0.0798   0.00692   0.00161  -0.0930   0.8688   0.0602
  -2.750   0.1073   0.00680   0.00149  -0.0928   0.8595   0.0688
  -2.500   0.1349   0.00670   0.00138  -0.0927   0.8505   0.0790
  -2.250   0.1623   0.00659   0.00128  -0.0925   0.8412   0.0963
  -2.000   0.1899   0.00645   0.00119  -0.0923   0.8309   0.1201
  -1.750   0.2173   0.00628   0.00111  -0.0922   0.8213   0.1557
  -1.500   0.2447   0.00613   0.00104  -0.0920   0.8116   0.1992
  -1.250   0.2721   0.00593   0.00099  -0.0919   0.8009   0.2583
  -1.000   0.2993   0.00571   0.00096  -0.0918   0.7895   0.3344
  -0.750   0.3265   0.00552   0.00094  -0.0916   0.7779   0.4104
  -0.500   0.3536   0.00536   0.00093  -0.0915   0.7663   0.4856
  -0.250   0.3805   0.00518   0.00094  -0.0912   0.7539   0.5698
   0.000   0.4071   0.00501   0.00096  -0.0909   0.7406   0.6543
   0.250   0.4331   0.00484   0.00100  -0.0904   0.7262   0.7423
   0.500   0.4581   0.00471   0.00104  -0.0895   0.7113   0.8221
   0.750   0.4785   0.00453   0.00108  -0.0875   0.6958   0.9256
   1.000   0.5146   0.00453   0.00105  -0.0891   0.6770   1.0000
   1.250   0.5414   0.00465   0.00108  -0.0887   0.6563   1.0000
   1.500   0.5681   0.00478   0.00111  -0.0884   0.6339   1.0000
   1.750   0.5945   0.00495   0.00116  -0.0880   0.6093   1.0000
   2.000   0.6211   0.00511   0.00121  -0.0877   0.5839   1.0000
   2.250   0.6476   0.00528   0.00128  -0.0873   0.5581   1.0000
   2.500   0.6736   0.00551   0.00137  -0.0869   0.5269   1.0000
   2.750   0.6996   0.00574   0.00147  -0.0865   0.4964   1.0000
   3.000   0.7254   0.00599   0.00159  -0.0861   0.4640   1.0000
   3.250   0.7509   0.00629   0.00172  -0.0856   0.4262   1.0000
   3.750   0.8019   0.00690   0.00204  -0.0848   0.3573   1.0000
   4.000   0.8270   0.00724   0.00222  -0.0843   0.3216   1.0000
   4.250   0.8524   0.00756   0.00240  -0.0839   0.2915   1.0000
   4.500   0.8775   0.00790   0.00261  -0.0834   0.2605   1.0000
   4.750   0.9026   0.00825   0.00283  -0.0830   0.2312   1.0000
   5.000   0.9277   0.00860   0.00305  -0.0825   0.2059   1.0000
   5.250   0.9530   0.00892   0.00327  -0.0821   0.1836   1.0000
   5.750   1.0032   0.00957   0.00376  -0.0812   0.1475   1.0000
   6.000   1.0283   0.00989   0.00402  -0.0808   0.1321   1.0000
   6.250   1.0534   0.01021   0.00428  -0.0803   0.1192   1.0000
   6.500   1.0783   0.01054   0.00457  -0.0799   0.1074   1.0000
   6.750   1.1030   0.01088   0.00485  -0.0794   0.0969   1.0000
   7.000   1.1281   0.01117   0.00514  -0.0789   0.0890   1.0000
   7.250   1.1527   0.01151   0.00545  -0.0784   0.0804   1.0000
   7.500   1.1766   0.01191   0.00580  -0.0778   0.0699   1.0000
   7.750   1.2006   0.01230   0.00614  -0.0772   0.0610   1.0000
   8.000   1.2245   0.01267   0.00650  -0.0766   0.0538   1.0000
   8.250   1.2478   0.01311   0.00691  -0.0760   0.0466   1.0000
   8.500   1.2710   0.01353   0.00732  -0.0753   0.0415   1.0000
   8.750   1.2940   0.01398   0.00778  -0.0745   0.0365   1.0000
   9.000   1.3168   0.01442   0.00821  -0.0738   0.0327   1.0000
   9.250   1.3384   0.01497   0.00876  -0.0729   0.0285   1.0000
   9.500   1.3614   0.01535   0.00918  -0.0722   0.0265   1.0000
   9.750   1.3824   0.01591   0.00974  -0.0712   0.0234   1.0000
  10.000   1.4033   0.01648   0.01035  -0.0702   0.0210   1.0000
  10.250   1.4248   0.01694   0.01084  -0.0693   0.0190   1.0000
  10.500   1.4427   0.01774   0.01165  -0.0679   0.0161   1.0000
  10.750   1.4632   0.01823   0.01220  -0.0668   0.0149   1.0000
  11.000   1.4825   0.01881   0.01281  -0.0657   0.0135   1.0000
  11.250   1.4980   0.01970   0.01373  -0.0639   0.0119   1.0000
  11.500   1.5141   0.02046   0.01457  -0.0623   0.0111   1.0000
  11.750   1.5306   0.02106   0.01525  -0.0607   0.0105   1.0000
  12.000   1.5444   0.02170   0.01595  -0.0586   0.0099   1.0000
  12.250   1.5559   0.02246   0.01675  -0.0563   0.0093   1.0000
  12.500   1.5634   0.02349   0.01786  -0.0535   0.0087   1.0000
  12.750   1.5642   0.02499   0.01948  -0.0500   0.0081   1.0000
  13.000   1.5748   0.02584   0.02042  -0.0480   0.0079   1.0000
  13.250   1.5831   0.02689   0.02156  -0.0459   0.0077   1.0000
  13.500   1.5903   0.02806   0.02283  -0.0438   0.0075   1.0000
  13.750   1.5965   0.02937   0.02422  -0.0418   0.0072   1.0000
  14.000   1.6012   0.03084   0.02581  -0.0399   0.0070   1.0000
  14.250   1.6060   0.03238   0.02743  -0.0382   0.0068   1.0000
  14.500   1.6080   0.03425   0.02940  -0.0366   0.0066   1.0000
  14.750   1.6091   0.03629   0.03155  -0.0352   0.0064   1.0000
  15.000   1.6063   0.03885   0.03421  -0.0340   0.0062   1.0000
  15.250   1.6002   0.04192   0.03741  -0.0331   0.0061   1.0000
  15.500   1.5879   0.04592   0.04156  -0.0327   0.0058   1.0000
  15.750   1.5716   0.05079   0.04661  -0.0330   0.0057   1.0000
  16.000   1.5525   0.05649   0.05249  -0.0342   0.0056   1.0000
  16.250   1.5414   0.06151   0.05766  -0.0358   0.0056   1.0000
  16.500   1.5330   0.06644   0.06272  -0.0377   0.0056   1.0000
  16.750   1.5214   0.07223   0.06866  -0.0402   0.0055   1.0000
  17.000   1.5084   0.07859   0.07516  -0.0433   0.0055   1.0000
  17.250   1.4902   0.08622   0.08294  -0.0472   0.0055   1.0000
  17.500   1.4658   0.09544   0.09233  -0.0522   0.0055   1.0000
  17.750   1.4439   0.10448   0.10153  -0.0573   0.0055   1.0000
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