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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 100,000
Max Cl/Cd: 51.9 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf6-il-100000.txt
Download as CSV file: xf-raf6-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 6 AIRFOIL                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3894   0.10260   0.09793  -0.0289   1.0000   0.0659
  -8.000  -0.4071   0.10113   0.09657  -0.0284   1.0000   0.0662
  -7.750  -0.4198   0.09900   0.09451  -0.0307   1.0000   0.0666
  -7.500  -0.4301   0.09688   0.09239  -0.0327   1.0000   0.0669
  -7.250  -0.4377   0.09481   0.09025  -0.0338   1.0000   0.0671
  -7.000  -0.4296   0.08834   0.08400  -0.0283   1.0000   0.0686
  -6.750  -0.4273   0.08546   0.08117  -0.0249   1.0000   0.0702
  -6.500  -0.4280   0.08282   0.07856  -0.0234   1.0000   0.0718
  -6.250  -0.4286   0.08009   0.07584  -0.0228   1.0000   0.0737
  -6.000  -0.4277   0.07718   0.07292  -0.0231   1.0000   0.0762
  -5.750  -0.4207   0.07465   0.07014  -0.0278   1.0000   0.0808
  -5.500  -0.4150   0.07068   0.06598  -0.0294   1.0000   0.0826
  -5.250  -0.4097   0.06685   0.06233  -0.0268   1.0000   0.0845
  -5.000  -0.4016   0.06422   0.05972  -0.0254   1.0000   0.0882
  -4.750  -0.3824   0.06166   0.05665  -0.0292   1.0000   0.0978
  -4.500  -0.3748   0.05792   0.05315  -0.0272   1.0000   0.1012
  -4.250  -0.3546   0.05571   0.05052  -0.0292   1.0000   0.1135
  -4.000  -0.3426   0.05236   0.04736  -0.0279   1.0000   0.1180
  -3.750  -0.3229   0.04973   0.04451  -0.0289   1.0000   0.1312
  -3.500  -0.3038   0.04736   0.04201  -0.0293   1.0000   0.1464
  -3.250  -0.2854   0.04505   0.03964  -0.0293   1.0000   0.1634
  -3.000  -0.2660   0.04322   0.03767  -0.0296   1.0000   0.1925
  -1.750  -0.0727   0.03184   0.02377  -0.0378   0.9896   0.1109
  -1.500  -0.0206   0.02989   0.02131  -0.0411   0.9844   0.0948
  -1.250   0.0233   0.02833   0.01950  -0.0437   0.9771   0.0916
  -1.000   0.0715   0.02714   0.01805  -0.0469   0.9697   0.0890
  -0.750   0.1283   0.02619   0.01693  -0.0517   0.9592   0.0949
  -0.500   0.1859   0.02475   0.01556  -0.0565   0.9473   0.1006
  -0.250   0.2333   0.02372   0.01458  -0.0596   0.9347   0.1139
   0.000   0.2739   0.02288   0.01381  -0.0617   0.9234   0.1388
   0.250   0.3186   0.02005   0.01332  -0.0634   0.9164   1.0000
   0.500   0.3673   0.01973   0.01267  -0.0667   0.9061   1.0000
   0.750   0.4073   0.01938   0.01215  -0.0684   0.8931   1.0000
   1.000   0.4485   0.01890   0.01156  -0.0702   0.8801   1.0000
   1.250   0.4910   0.01828   0.01086  -0.0720   0.8670   1.0000
   1.500   0.5357   0.01750   0.01002  -0.0741   0.8539   1.0000
   1.750   0.5825   0.01665   0.00912  -0.0764   0.8389   1.0000
   2.000   0.6298   0.01580   0.00823  -0.0787   0.8207   1.0000
   2.250   0.6686   0.01521   0.00759  -0.0795   0.7939   1.0000
   2.500   0.7062   0.01473   0.00700  -0.0801   0.7563   1.0000
   2.750   0.7311   0.01453   0.00665  -0.0783   0.6968   1.0000
   3.000   0.7583   0.01461   0.00620  -0.0769   0.6034   1.0000
   3.250   0.7791   0.01534   0.00625  -0.0749   0.5225   1.0000
   3.500   0.7992   0.01622   0.00663  -0.0733   0.4725   1.0000
   3.750   0.8215   0.01706   0.00708  -0.0722   0.4392   1.0000
   4.000   0.8448   0.01778   0.00760  -0.0714   0.4138   1.0000
   4.250   0.8693   0.01850   0.00811  -0.0708   0.3948   1.0000
   4.500   0.8941   0.01918   0.00866  -0.0703   0.3789   1.0000
   4.750   0.9188   0.01981   0.00922  -0.0698   0.3650   1.0000
   5.000   0.9436   0.02044   0.00982  -0.0694   0.3531   1.0000
   5.250   0.9689   0.02111   0.01043  -0.0690   0.3426   1.0000
   5.500   0.9947   0.02178   0.01103  -0.0688   0.3329   1.0000
   5.750   1.0187   0.02242   0.01175  -0.0682   0.3235   1.0000
   6.000   1.0452   0.02319   0.01242  -0.0682   0.3156   1.0000
   6.250   1.0684   0.02383   0.01321  -0.0674   0.3070   1.0000
   6.500   1.0944   0.02465   0.01398  -0.0673   0.2998   1.0000
   6.750   1.1175   0.02538   0.01485  -0.0666   0.2923   1.0000
   7.000   1.1441   0.02628   0.01568  -0.0666   0.2858   1.0000
   7.250   1.1653   0.02705   0.01670  -0.0656   0.2785   1.0000
   7.500   1.1921   0.02798   0.01755  -0.0657   0.2724   1.0000
   7.750   1.2125   0.02897   0.01883  -0.0646   0.2664   1.0000
   8.000   1.2357   0.02989   0.01987  -0.0640   0.2604   1.0000
   8.250   1.2594   0.03105   0.02110  -0.0636   0.2550   1.0000
   8.500   1.2781   0.03210   0.02243  -0.0623   0.2490   1.0000
   8.750   1.3022   0.03317   0.02356  -0.0620   0.2440   1.0000
   9.000   1.3219   0.03466   0.02529  -0.0610   0.2397   1.0000
   9.250   1.3376   0.03611   0.02708  -0.0593   0.2350   1.0000
   9.500   1.3589   0.03735   0.02847  -0.0586   0.2306   1.0000
   9.750   1.3811   0.03880   0.02999  -0.0581   0.2262   1.0000
  10.000   1.3883   0.04016   0.03181  -0.0552   0.2204   1.0000
  10.250   1.4186   0.04012   0.03150  -0.0558   0.2120   1.0000
  10.500   1.4210   0.04114   0.03299  -0.0521   0.2053   1.0000
  10.750   1.4511   0.04089   0.03251  -0.0527   0.1977   1.0000
  11.000   1.4514   0.04211   0.03422  -0.0488   0.1921   1.0000
  11.250   1.4747   0.04146   0.03348  -0.0482   0.1843   1.0000
  11.500   1.4784   0.04236   0.03472  -0.0448   0.1784   1.0000
  11.750   1.4955   0.04129   0.03357  -0.0431   0.1700   1.0000
  12.000   1.4910   0.04171   0.03434  -0.0385   0.1629   1.0000
  12.250   1.4962   0.04061   0.03313  -0.0349   0.1547   1.0000
  12.500   1.4838   0.04129   0.03422  -0.0294   0.1476   1.0000
  12.750   1.4764   0.04138   0.03446  -0.0249   0.1387   1.0000
  13.000   1.4659   0.04208   0.03533  -0.0210   0.1269   1.0000
  13.250   1.4545   0.04376   0.03721  -0.0179   0.1091   1.0000
  13.500   1.4396   0.04662   0.04000  -0.0156   0.0922   1.0000
  13.750   1.4233   0.05042   0.04383  -0.0141   0.0795   1.0000
  14.000   1.4061   0.05474   0.04821  -0.0132   0.0722   1.0000
  14.250   1.3881   0.05954   0.05311  -0.0130   0.0678   1.0000
  14.500   1.3699   0.06482   0.05854  -0.0137   0.0646   1.0000
  14.750   1.3497   0.07082   0.06467  -0.0153   0.0626   1.0000
  15.000   1.3292   0.07737   0.07134  -0.0177   0.0614   1.0000
  15.250   1.3090   0.08419   0.07823  -0.0204   0.0602   1.0000
  15.500   1.2912   0.09095   0.08517  -0.0231   0.0589   1.0000
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