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S4110 (s4110-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 500,000
Max Cl/Cd: 107.22 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4110-il-500000.txt
Download as CSV file: xf-s4110-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4055   0.08959   0.08730  -0.0346   1.0000   0.0228
  -8.750  -0.4050   0.08654   0.08428  -0.0347   1.0000   0.0230
  -8.500  -0.4017   0.08449   0.08225  -0.0341   1.0000   0.0234
  -8.250  -0.4024   0.08192   0.07972  -0.0338   1.0000   0.0237
  -8.000  -0.4028   0.08006   0.07789  -0.0328   1.0000   0.0242
  -7.750  -0.4124   0.07790   0.07578  -0.0313   1.0000   0.0245
  -7.500  -0.4289   0.07617   0.07413  -0.0286   1.0000   0.0246
  -7.250  -0.4410   0.07386   0.07187  -0.0277   0.9999   0.0248
  -7.000  -0.4137   0.06767   0.06566  -0.0386   0.9960   0.0260
  -6.750  -0.3699   0.05522   0.05301  -0.0606   0.9899   0.0294
  -6.500  -0.3474   0.03987   0.03712  -0.0766   0.9842   0.0305
  -6.250  -0.3321   0.01978   0.01517  -0.0837   0.9762   0.0164
  -6.000  -0.2988   0.01726   0.01223  -0.0856   0.9737   0.0164
  -5.750  -0.2631   0.01584   0.01054  -0.0874   0.9720   0.0168
  -5.500  -0.2280   0.01377   0.00818  -0.0894   0.9706   0.0173
  -5.250  -0.1996   0.01268   0.00697  -0.0896   0.9651   0.0181
  -5.000  -0.1651   0.01196   0.00620  -0.0911   0.9621   0.0190
  -4.750  -0.1300   0.01134   0.00552  -0.0926   0.9595   0.0203
  -4.500  -0.0944   0.01090   0.00500  -0.0941   0.9571   0.0221
  -4.250  -0.0665   0.01018   0.00424  -0.0941   0.9505   0.0249
  -4.000  -0.0344   0.00966   0.00370  -0.0948   0.9459   0.0321
  -3.750  -0.0025   0.00933   0.00342  -0.0954   0.9415   0.0506
  -3.500   0.0254   0.00911   0.00321  -0.0953   0.9340   0.0606
  -3.250   0.0561   0.00885   0.00296  -0.0957   0.9287   0.0698
  -3.000   0.0831   0.00868   0.00278  -0.0954   0.9201   0.0799
  -2.750   0.1122   0.00847   0.00256  -0.0954   0.9136   0.0919
  -2.500   0.1389   0.00824   0.00238  -0.0951   0.9043   0.1094
  -2.250   0.1666   0.00800   0.00220  -0.0949   0.8963   0.1362
  -2.000   0.1937   0.00772   0.00205  -0.0946   0.8874   0.1809
  -1.750   0.2204   0.00740   0.00194  -0.0944   0.8781   0.2529
  -1.500   0.2473   0.00706   0.00186  -0.0942   0.8692   0.3493
  -1.250   0.2735   0.00675   0.00182  -0.0938   0.8588   0.4467
  -1.000   0.2998   0.00648   0.00180  -0.0934   0.8486   0.5436
  -0.750   0.3255   0.00620   0.00179  -0.0928   0.8390   0.6457
  -0.500   0.3499   0.00594   0.00180  -0.0918   0.8283   0.7459
  -0.250   0.3715   0.00568   0.00182  -0.0899   0.8166   0.8486
   0.000   0.3992   0.00549   0.00176  -0.0891   0.8053   0.9566
   0.250   0.4357   0.00549   0.00168  -0.0908   0.7937   1.0000
   0.500   0.4625   0.00556   0.00165  -0.0904   0.7813   1.0000
   0.750   0.4893   0.00563   0.00163  -0.0900   0.7680   1.0000
   1.000   0.5161   0.00570   0.00163  -0.0896   0.7537   1.0000
   1.250   0.5428   0.00578   0.00163  -0.0892   0.7385   1.0000
   1.500   0.5695   0.00587   0.00165  -0.0888   0.7220   1.0000
   1.750   0.5960   0.00597   0.00168  -0.0883   0.7039   1.0000
   2.000   0.6222   0.00610   0.00171  -0.0878   0.6838   1.0000
   2.250   0.6485   0.00623   0.00175  -0.0874   0.6621   1.0000
   2.750   0.7003   0.00656   0.00190  -0.0863   0.6140   1.0000
   3.000   0.7259   0.00677   0.00199  -0.0857   0.5862   1.0000
   3.250   0.7509   0.00701   0.00210  -0.0851   0.5545   1.0000
   3.500   0.7758   0.00729   0.00225  -0.0845   0.5225   1.0000
   3.750   0.8004   0.00759   0.00241  -0.0838   0.4854   1.0000
   4.000   0.8246   0.00795   0.00259  -0.0831   0.4463   1.0000
   4.250   0.8487   0.00833   0.00281  -0.0824   0.4073   1.0000
   4.500   0.8726   0.00875   0.00306  -0.0818   0.3663   1.0000
   4.750   0.8965   0.00917   0.00331  -0.0811   0.3290   1.0000
   5.000   0.9202   0.00963   0.00359  -0.0804   0.2924   1.0000
   5.250   0.9441   0.01007   0.00389  -0.0798   0.2582   1.0000
   5.500   0.9679   0.01052   0.00421  -0.0792   0.2279   1.0000
   5.750   0.9917   0.01097   0.00453  -0.0786   0.2017   1.0000
   6.000   1.0154   0.01143   0.00487  -0.0779   0.1780   1.0000
   6.250   1.0394   0.01184   0.00522  -0.0773   0.1591   1.0000
   6.500   1.0633   0.01227   0.00560  -0.0767   0.1427   1.0000
   6.750   1.0870   0.01270   0.00598  -0.0761   0.1280   1.0000
   7.000   1.1107   0.01313   0.00637  -0.0754   0.1159   1.0000
   7.250   1.1341   0.01357   0.00678  -0.0748   0.1046   1.0000
   7.500   1.1571   0.01405   0.00724  -0.0740   0.0940   1.0000
   7.750   1.1799   0.01454   0.00770  -0.0733   0.0840   1.0000
   8.000   1.2030   0.01498   0.00815  -0.0725   0.0751   1.0000
   8.250   1.2253   0.01550   0.00866  -0.0717   0.0660   1.0000
   8.500   1.2464   0.01612   0.00924  -0.0708   0.0575   1.0000
   8.750   1.2683   0.01663   0.00978  -0.0699   0.0510   1.0000
   9.000   1.2888   0.01727   0.01044  -0.0688   0.0455   1.0000
   9.250   1.3094   0.01787   0.01106  -0.0678   0.0409   1.0000
   9.500   1.3275   0.01870   0.01193  -0.0664   0.0366   1.0000
   9.750   1.3481   0.01924   0.01254  -0.0653   0.0334   1.0000
  10.000   1.3638   0.02021   0.01350  -0.0636   0.0295   1.0000
  10.250   1.3821   0.02089   0.01430  -0.0623   0.0271   1.0000
  10.500   1.3998   0.02158   0.01504  -0.0609   0.0247   1.0000
  10.750   1.4095   0.02282   0.01632  -0.0584   0.0221   1.0000
  11.000   1.4203   0.02378   0.01740  -0.0559   0.0207   1.0000
  11.250   1.4327   0.02460   0.01831  -0.0537   0.0193   1.0000
  11.500   1.4441   0.02547   0.01925  -0.0516   0.0180   1.0000
  11.750   1.4503   0.02672   0.02056  -0.0490   0.0168   1.0000
  12.000   1.4456   0.02888   0.02284  -0.0453   0.0157   1.0000
  12.250   1.4563   0.02989   0.02397  -0.0436   0.0152   1.0000
  12.500   1.4634   0.03123   0.02546  -0.0416   0.0145   1.0000
  12.750   1.4685   0.03279   0.02714  -0.0397   0.0139   1.0000
  13.000   1.4731   0.03444   0.02889  -0.0381   0.0133   1.0000
  13.250   1.4759   0.03632   0.03087  -0.0365   0.0129   1.0000
  13.500   1.4768   0.03848   0.03313  -0.0352   0.0125   1.0000
  13.750   1.4724   0.04132   0.03609  -0.0339   0.0120   1.0000
  14.000   1.4609   0.04516   0.04010  -0.0329   0.0116   1.0000
  14.250   1.4522   0.04897   0.04408  -0.0325   0.0113   1.0000
  14.500   1.4503   0.05211   0.04737  -0.0325   0.0112   1.0000
  14.750   1.4485   0.05539   0.05080  -0.0330   0.0109   1.0000
  15.000   1.4443   0.05917   0.05474  -0.0338   0.0107   1.0000
  15.250   1.4358   0.06378   0.05951  -0.0350   0.0105   1.0000
  15.500   1.4279   0.06858   0.06447  -0.0368   0.0103   1.0000
  15.750   1.4172   0.07411   0.07017  -0.0391   0.0102   1.0000
  16.000   1.4058   0.08006   0.07628  -0.0419   0.0100   1.0000
  16.250   1.3924   0.08669   0.08308  -0.0452   0.0100   1.0000
  16.500   1.3781   0.09376   0.09031  -0.0489   0.0099   1.0000
  16.750   1.3629   0.10132   0.09803  -0.0531   0.0098   1.0000
  17.000   1.3470   0.10930   0.10616  -0.0577   0.0098   1.0000
  17.250   1.3296   0.11782   0.11484  -0.0627   0.0098   1.0000
  17.500   1.3110   0.12685   0.12404  -0.0681   0.0098   1.0000
  17.750   1.2923   0.13625   0.13359  -0.0739   0.0098   1.0000
  18.000   1.2723   0.14623   0.14373  -0.0801   0.0099   1.0000
  18.250   1.2504   0.15714   0.15480  -0.0871   0.0100   1.0000
  18.500   1.2196   0.17120   0.16904  -0.0961   0.0102   1.0000
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