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SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD6060-104-88 (sd6060-il)
Reynolds number: 100,000
Max Cl/Cd: 51.6 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6060-il-100000.txt
Download as CSV file: xf-sd6060-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD6060-104-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4707   0.11441   0.10952  -0.0152   1.0000   0.0926
 -10.000  -0.4817   0.11116   0.10634  -0.0200   1.0000   0.0945
  -9.750  -0.5001   0.10769   0.10299  -0.0265   1.0000   0.0952
  -9.500  -0.4621   0.10295   0.09817  -0.0193   1.0000   0.1010
  -9.250  -0.4632   0.09941   0.09469  -0.0215   1.0000   0.1058
  -9.000  -0.4926   0.09565   0.09109  -0.0303   1.0000   0.1087
  -8.750  -0.4750   0.09098   0.08642  -0.0275   1.0000   0.1113
  -8.500  -0.4625   0.08788   0.08331  -0.0262   1.0000   0.1156
  -8.250  -0.4739   0.08396   0.07948  -0.0303   1.0000   0.1206
  -8.000  -0.5174   0.08003   0.07560  -0.0385   1.0000   0.1227
  -7.750  -0.4920   0.07563   0.07129  -0.0349   1.0000   0.1264
  -7.500  -0.4889   0.07248   0.06817  -0.0347   1.0000   0.1317
  -7.250  -0.5216   0.06864   0.06423  -0.0382   1.0000   0.1381
  -7.000  -0.5027   0.06542   0.06114  -0.0354   1.0000   0.1420
  -6.750  -0.5369   0.06423   0.05964  -0.0345   1.0000   0.1516
  -6.500  -0.5207   0.06010   0.05578  -0.0317   1.0000   0.1548
  -6.250  -0.5233   0.05797   0.05364  -0.0289   1.0000   0.1606
  -5.750  -0.5362   0.04412   0.03820  -0.0259   1.0000   0.0805
  -5.500  -0.5345   0.04417   0.03850  -0.0242   1.0000   0.1110
  -5.250  -0.5160   0.03507   0.02776  -0.0201   1.0000   0.0549
  -5.000  -0.5024   0.03191   0.02435  -0.0185   1.0000   0.0535
  -4.750  -0.4862   0.02941   0.02147  -0.0168   1.0000   0.0526
  -4.500  -0.4677   0.02739   0.01905  -0.0152   1.0000   0.0530
  -4.250  -0.4484   0.02631   0.01753  -0.0136   1.0000   0.0556
  -4.000  -0.4229   0.02397   0.01513  -0.0137   0.9986   0.0594
  -3.750  -0.3826   0.02236   0.01335  -0.0158   0.9931   0.0650
  -3.500  -0.3449   0.02094   0.01190  -0.0177   0.9869   0.0794
  -3.250  -0.3092   0.01934   0.01056  -0.0195   0.9808   0.1217
  -3.000  -0.2820   0.01688   0.00955  -0.0204   0.9741   0.3268
  -2.750  -0.2642   0.01555   0.01012  -0.0169   0.9676   0.7437
  -2.500  -0.2345   0.01601   0.01065  -0.0147   0.9602   0.8685
  -2.250  -0.1685   0.01684   0.01117  -0.0194   0.9586   0.9421
  -2.000  -0.0531   0.01729   0.01111  -0.0350   0.9639   0.9795
  -1.750   0.0379   0.01712   0.01059  -0.0477   0.9652   1.0000
  -1.500   0.0859   0.01704   0.01031  -0.0528   0.9576   1.0000
  -1.250   0.1241   0.01699   0.01011  -0.0559   0.9473   1.0000
  -1.000   0.1688   0.01692   0.00991  -0.0601   0.9392   1.0000
  -0.750   0.2133   0.01683   0.00970  -0.0640   0.9310   1.0000
  -0.500   0.2468   0.01681   0.00961  -0.0658   0.9202   1.0000
  -0.250   0.2829   0.01677   0.00949  -0.0679   0.9107   1.0000
   0.000   0.3191   0.01667   0.00934  -0.0698   0.9014   1.0000
   0.250   0.3426   0.01673   0.00936  -0.0693   0.8891   1.0000
   0.500   0.3652   0.01679   0.00939  -0.0686   0.8770   1.0000
   0.750   0.3877   0.01684   0.00941  -0.0677   0.8654   1.0000
   1.000   0.4113   0.01684   0.00940  -0.0668   0.8546   1.0000
   1.250   0.4346   0.01681   0.00935  -0.0656   0.8440   1.0000
   1.500   0.4522   0.01692   0.00946  -0.0637   0.8312   1.0000
   1.750   0.4704   0.01703   0.00957  -0.0617   0.8189   1.0000
   2.000   0.4895   0.01711   0.00967  -0.0599   0.8068   1.0000
   2.250   0.5097   0.01714   0.00969  -0.0580   0.7952   1.0000
   2.500   0.5317   0.01707   0.00963  -0.0563   0.7843   1.0000
   2.750   0.5530   0.01703   0.00959  -0.0545   0.7724   1.0000
   3.000   0.5729   0.01705   0.00967  -0.0525   0.7591   1.0000
   3.250   0.5935   0.01705   0.00969  -0.0507   0.7456   1.0000
   3.500   0.6148   0.01701   0.00968  -0.0488   0.7318   1.0000
   3.750   0.6367   0.01695   0.00964  -0.0470   0.7175   1.0000
   4.000   0.6591   0.01686   0.00961  -0.0453   0.7028   1.0000
   4.250   0.6821   0.01675   0.00952  -0.0436   0.6873   1.0000
   4.500   0.7044   0.01669   0.00951  -0.0419   0.6700   1.0000
   4.750   0.7262   0.01667   0.00954  -0.0402   0.6507   1.0000
   5.000   0.7499   0.01655   0.00947  -0.0386   0.6314   1.0000
   5.250   0.7721   0.01653   0.00950  -0.0369   0.6088   1.0000
   5.500   0.7952   0.01647   0.00944  -0.0353   0.5850   1.0000
   5.750   0.8173   0.01647   0.00946  -0.0336   0.5575   1.0000
   6.000   0.8379   0.01655   0.00962  -0.0318   0.5250   1.0000
   6.250   0.8583   0.01669   0.00972  -0.0300   0.4890   1.0000
   6.500   0.8772   0.01700   0.00995  -0.0281   0.4475   1.0000
   6.750   0.8948   0.01751   0.01030  -0.0261   0.4029   1.0000
   7.000   0.9108   0.01822   0.01085  -0.0241   0.3561   1.0000
   7.250   0.9245   0.01906   0.01147  -0.0220   0.3066   1.0000
   7.500   0.9364   0.01999   0.01221  -0.0198   0.2548   1.0000
   7.750   0.9481   0.02108   0.01309  -0.0177   0.2084   1.0000
   8.000   0.9571   0.02251   0.01426  -0.0154   0.1606   1.0000
   8.250   0.9604   0.02457   0.01589  -0.0123   0.1112   1.0000
   8.500   0.9665   0.02661   0.01767  -0.0096   0.0848   1.0000
   8.750   0.9791   0.02857   0.01954  -0.0076   0.0724   1.0000
   9.000   0.9993   0.03053   0.02160  -0.0063   0.0651   1.0000
   9.250   1.0208   0.03291   0.02391  -0.0057   0.0586   1.0000
   9.500   1.0423   0.03491   0.02620  -0.0047   0.0544   1.0000
   9.750   1.0646   0.03743   0.02892  -0.0040   0.0516   1.0000
  10.000   1.0860   0.04047   0.03210  -0.0034   0.0494   1.0000
  10.250   1.0990   0.04447   0.03640  -0.0023   0.0473   1.0000
  10.500   1.1028   0.04692   0.03933   0.0002   0.0460   1.0000
  10.750   1.1039   0.05018   0.04301   0.0026   0.0455   1.0000
  11.000   1.0998   0.05374   0.04697   0.0051   0.0454   1.0000
  11.250   1.0898   0.05713   0.05067   0.0079   0.0455   1.0000
  11.500   1.0756   0.06069   0.05451   0.0104   0.0458   1.0000
  11.750   1.0601   0.06447   0.05854   0.0121   0.0461   1.0000
  12.000   1.0425   0.06862   0.06291   0.0129   0.0464   1.0000
  12.250   1.0234   0.07323   0.06771   0.0127   0.0467   1.0000
  12.500   1.0045   0.07832   0.07297   0.0117   0.0471   1.0000
  12.750   0.9858   0.08418   0.07897   0.0099   0.0475   1.0000
  13.250   0.8627   0.11282   0.10815  -0.0121   0.0550   1.0000
  13.500   0.8450   0.12330   0.11859  -0.0176   0.0575   1.0000
  13.750   0.8401   0.13018   0.12545  -0.0203   0.0586   1.0000
  14.000   0.8397   0.13596   0.13122  -0.0219   0.0593   1.0000
  14.250   0.6535   0.15479   0.15040  -0.0286   0.1235   1.0000
  14.500   0.6434   0.15868   0.15426  -0.0315   0.1227   1.0000
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