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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 500,000
Max Cl/Cd: 60.19 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6063-il-500000-n5.txt
Download as CSV file: xf-s6063-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5591   0.07473   0.07260  -0.0108   1.0000   0.0066
  -7.750  -0.5634   0.06900   0.06690  -0.0168   1.0000   0.0063
  -7.500  -0.5601   0.06246   0.06032  -0.0233   1.0000   0.0063
  -7.250  -0.5545   0.05541   0.05315  -0.0286   1.0000   0.0063
  -7.000  -0.5457   0.04878   0.04636  -0.0322   1.0000   0.0064
  -6.000  -0.4882   0.02799   0.02431  -0.0351   1.0000   0.0067
  -5.750  -0.4714   0.02402   0.01989  -0.0343   1.0000   0.0064
  -5.500  -0.4523   0.02110   0.01658  -0.0333   0.9997   0.0063
  -5.250  -0.4213   0.01834   0.01338  -0.0345   0.9931   0.0061
  -5.000  -0.3897   0.01627   0.01093  -0.0355   0.9870   0.0061
  -4.750  -0.3580   0.01465   0.00904  -0.0363   0.9810   0.0061
  -4.500  -0.3267   0.01336   0.00754  -0.0371   0.9741   0.0061
  -4.250  -0.2961   0.01231   0.00634  -0.0377   0.9666   0.0063
  -4.000  -0.2659   0.01147   0.00539  -0.0381   0.9584   0.0065
  -3.750  -0.2378   0.01083   0.00463  -0.0381   0.9484   0.0068
  -3.500  -0.2103   0.01036   0.00409  -0.0379   0.9379   0.0071
  -3.250  -0.1842   0.00968   0.00329  -0.0375   0.9270   0.0077
  -3.000  -0.1582   0.00923   0.00275  -0.0370   0.9161   0.0095
  -2.750  -0.1318   0.00896   0.00238  -0.0365   0.9047   0.0102
  -2.500  -0.1052   0.00874   0.00206  -0.0361   0.8934   0.0109
  -2.250  -0.0786   0.00856   0.00180  -0.0356   0.8816   0.0123
  -2.000  -0.0522   0.00829   0.00157  -0.0352   0.8692   0.0351
  -1.750  -0.0264   0.00782   0.00137  -0.0349   0.8561   0.1164
  -1.500  -0.0007   0.00735   0.00122  -0.0347   0.8426   0.2213
  -1.250   0.0251   0.00690   0.00112  -0.0344   0.8287   0.3366
  -1.000   0.0491   0.00615   0.00106  -0.0340   0.8141   0.5450
  -0.750   0.0747   0.00589   0.00102  -0.0335   0.7983   0.6296
  -0.500   0.1000   0.00568   0.00099  -0.0328   0.7814   0.7047
  -0.250   0.1249   0.00552   0.00098  -0.0320   0.7636   0.7711
   0.000   0.1494   0.00542   0.00098  -0.0309   0.7450   0.8276
   0.250   0.1733   0.00535   0.00098  -0.0297   0.7250   0.8795
   0.500   0.1991   0.00535   0.00098  -0.0289   0.7035   0.9264
   0.750   0.2323   0.00541   0.00096  -0.0298   0.6780   0.9609
   1.000   0.2685   0.00551   0.00095  -0.0316   0.6491   0.9858
   1.250   0.3013   0.00564   0.00095  -0.0328   0.6192   1.0000
   1.500   0.3273   0.00580   0.00100  -0.0324   0.5902   1.0000
   1.750   0.3534   0.00597   0.00105  -0.0320   0.5603   1.0000
   2.000   0.3786   0.00629   0.00112  -0.0316   0.5020   1.0000
   2.250   0.4027   0.00684   0.00123  -0.0311   0.4044   1.0000
   2.500   0.4281   0.00722   0.00138  -0.0308   0.3451   1.0000
   2.750   0.4537   0.00762   0.00154  -0.0306   0.2866   1.0000
   3.000   0.4788   0.00812   0.00174  -0.0303   0.2173   1.0000
   3.250   0.5033   0.00878   0.00201  -0.0300   0.1322   1.0000
   3.500   0.5269   0.00966   0.00244  -0.0297   0.0360   1.0000
   3.750   0.5529   0.01008   0.00275  -0.0294   0.0137   1.0000
   4.000   0.5796   0.01033   0.00303  -0.0292   0.0120   1.0000
   4.250   0.6061   0.01061   0.00336  -0.0290   0.0111   1.0000
   4.500   0.6325   0.01094   0.00377  -0.0287   0.0105   1.0000
   4.750   0.6587   0.01131   0.00421  -0.0284   0.0100   1.0000
   5.000   0.6846   0.01174   0.00471  -0.0281   0.0097   1.0000
   5.250   0.7101   0.01224   0.00528  -0.0277   0.0095   1.0000
   5.500   0.7353   0.01281   0.00592  -0.0273   0.0092   1.0000
   5.750   0.7600   0.01345   0.00665  -0.0269   0.0086   1.0000
   6.000   0.7836   0.01430   0.00758  -0.0263   0.0080   1.0000
   6.250   0.8065   0.01529   0.00866  -0.0256   0.0077   1.0000
   6.500   0.8283   0.01660   0.01009  -0.0248   0.0075   1.0000
   6.750   0.8499   0.01812   0.01175  -0.0239   0.0072   1.0000
   7.000   0.8734   0.01909   0.01285  -0.0233   0.0071   1.0000
   7.250   0.8966   0.02015   0.01405  -0.0227   0.0069   1.0000
   7.500   0.9190   0.02145   0.01552  -0.0219   0.0068   1.0000
   7.750   0.9404   0.02301   0.01731  -0.0211   0.0067   1.0000
   8.000   0.9607   0.02481   0.01936  -0.0202   0.0066   1.0000
   8.250   0.9793   0.02691   0.02173  -0.0192   0.0065   1.0000
   8.500   0.9957   0.02932   0.02446  -0.0180   0.0065   1.0000
   8.750   1.0092   0.03208   0.02756  -0.0167   0.0065   1.0000
   9.000   1.0193   0.03514   0.03097  -0.0153   0.0065   1.0000
   9.250   1.0280   0.03796   0.03409  -0.0139   0.0064   1.0000
   9.500   1.0317   0.04121   0.03766  -0.0123   0.0063   1.0000
   9.750   1.0323   0.04438   0.04110  -0.0107   0.0061   1.0000
  10.000   1.0266   0.04767   0.04464  -0.0089   0.0059   1.0000
  10.250   1.0098   0.05105   0.04822  -0.0066   0.0059   1.0000
  10.500   0.9905   0.05516   0.05252  -0.0063   0.0060   1.0000
  10.750   0.9698   0.06051   0.05803  -0.0087   0.0060   1.0000
  11.000   0.9495   0.06745   0.06512  -0.0138   0.0061   1.0000
  11.250   0.9245   0.07821   0.07604  -0.0229   0.0062   1.0000
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