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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 50,000
Max Cl/Cd: 36.66 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf6-il-50000-n5.txt
Download as CSV file: xf-raf6-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3588   0.10817   0.10203  -0.0255   1.0000   0.0821
  -7.500  -0.3740   0.10695   0.10094  -0.0242   1.0000   0.0833
  -7.250  -0.3876   0.10559   0.09970  -0.0254   1.0000   0.0845
  -7.000  -0.3980   0.10401   0.09819  -0.0279   1.0000   0.0851
  -6.750  -0.3970   0.10006   0.09433  -0.0259   1.0000   0.0862
  -6.500  -0.3930   0.09655   0.09087  -0.0221   1.0000   0.0885
  -6.250  -0.3931   0.09387   0.08823  -0.0210   1.0000   0.0913
  -6.000  -0.3936   0.09123   0.08563  -0.0217   1.0000   0.0950
  -5.750  -0.3908   0.08971   0.08390  -0.0305   1.0000   0.0995
  -5.500  -0.3890   0.08499   0.07940  -0.0246   1.0000   0.1023
  -5.250  -0.3841   0.08211   0.07655  -0.0232   1.0000   0.1075
  -4.750  -0.3625   0.07560   0.06996  -0.0269   0.9986   0.1236
  -4.500  -0.3326   0.07165   0.06579  -0.0343   0.9937   0.1420
  -4.250  -0.3113   0.06799   0.06212  -0.0360   0.9897   0.1564
  -4.000  -0.2874   0.06469   0.05877  -0.0381   0.9856   0.1747
  -3.500  -0.1786   0.05323   0.04583  -0.0527   0.9779   0.0610
  -3.250  -0.1485   0.04999   0.04236  -0.0549   0.9736   0.0586
  -3.000  -0.1119   0.04694   0.03892  -0.0577   0.9699   0.0568
  -2.750  -0.0752   0.04412   0.03560  -0.0601   0.9658   0.0541
  -2.500  -0.0360   0.04161   0.03242  -0.0621   0.9615   0.0513
  -2.250   0.0028   0.03952   0.02986  -0.0644   0.9579   0.0516
  -2.000   0.0353   0.03786   0.02789  -0.0656   0.9522   0.0541
  -1.750   0.0771   0.03621   0.02580  -0.0680   0.9476   0.0555
  -1.500   0.1136   0.03480   0.02398  -0.0692   0.9392   0.0575
  -1.250   0.1533   0.03368   0.02237  -0.0707   0.9307   0.0619
  -1.000   0.1950   0.03232   0.02089  -0.0727   0.9234   0.0663
  -0.750   0.2287   0.03154   0.01985  -0.0733   0.9136   0.0739
  -0.500   0.2671   0.03069   0.01886  -0.0750   0.9063   0.0834
  -0.250   0.3016   0.02999   0.01806  -0.0761   0.8971   0.0976
   0.250   0.3712   0.02633   0.01682  -0.0778   0.8797   1.0000
   0.500   0.4046   0.02625   0.01628  -0.0783   0.8660   1.0000
   0.750   0.4415   0.02597   0.01567  -0.0793   0.8511   1.0000
   1.000   0.4791   0.02556   0.01499  -0.0802   0.8356   1.0000
   1.250   0.5156   0.02511   0.01434  -0.0809   0.8201   1.0000
   1.500   0.5504   0.02470   0.01376  -0.0812   0.8048   1.0000
   1.750   0.5835   0.02437   0.01331  -0.0814   0.7891   1.0000
   2.000   0.6147   0.02410   0.01294  -0.0813   0.7719   1.0000
   2.250   0.6450   0.02383   0.01259  -0.0809   0.7530   1.0000
   2.500   0.6722   0.02363   0.01233  -0.0801   0.7310   1.0000
   2.750   0.6958   0.02353   0.01218  -0.0787   0.7048   1.0000
   3.000   0.7214   0.02339   0.01199  -0.0776   0.6751   1.0000
   3.250   0.7521   0.02312   0.01161  -0.0772   0.6416   1.0000
   3.500   0.7856   0.02288   0.01117  -0.0772   0.6022   1.0000
   3.750   0.8181   0.02285   0.01083  -0.0772   0.5592   1.0000
   4.000   0.8453   0.02316   0.01081  -0.0765   0.5180   1.0000
   4.250   0.8692   0.02371   0.01105  -0.0756   0.4830   1.0000
   4.500   0.8918   0.02437   0.01146  -0.0746   0.4545   1.0000
   4.750   0.9141   0.02509   0.01197  -0.0737   0.4306   1.0000
   5.000   0.9370   0.02582   0.01256  -0.0730   0.4104   1.0000
   5.250   0.9602   0.02655   0.01319  -0.0724   0.3924   1.0000
   5.500   0.9845   0.02728   0.01384  -0.0720   0.3770   1.0000
   5.750   1.0091   0.02800   0.01455  -0.0716   0.3631   1.0000
   6.000   1.0336   0.02872   0.01531  -0.0713   0.3501   1.0000
   6.250   1.0591   0.02947   0.01610  -0.0712   0.3389   1.0000
   6.750   1.1092   0.03100   0.01774  -0.0708   0.3189   1.0000
   7.000   1.1347   0.03179   0.01857  -0.0707   0.3104   1.0000
   7.250   1.1585   0.03264   0.01957  -0.0703   0.3018   1.0000
   7.500   1.1842   0.03351   0.02049  -0.0702   0.2946   1.0000
   7.750   1.2061   0.03445   0.02164  -0.0696   0.2866   1.0000
   8.000   1.2313   0.03536   0.02258  -0.0695   0.2799   1.0000
   8.250   1.2508   0.03643   0.02393  -0.0686   0.2726   1.0000
   8.500   1.2754   0.03741   0.02502  -0.0684   0.2668   1.0000
   8.750   1.2940   0.03863   0.02652  -0.0674   0.2605   1.0000
   9.000   1.3139   0.03977   0.02786  -0.0665   0.2545   1.0000
   9.250   1.3371   0.04092   0.02913  -0.0662   0.2494   1.0000
   9.500   1.3503   0.04244   0.03108  -0.0645   0.2441   1.0000
   9.750   1.3689   0.04376   0.03263  -0.0635   0.2392   1.0000
  10.000   1.3918   0.04504   0.03405  -0.0632   0.2351   1.0000
  10.250   1.3968   0.04694   0.03642  -0.0605   0.2305   1.0000
  10.500   1.4078   0.04867   0.03849  -0.0587   0.2265   1.0000
  10.750   1.4246   0.05026   0.04034  -0.0577   0.2233   1.0000
  11.000   1.4340   0.05175   0.04213  -0.0556   0.2186   1.0000
  11.250   1.4237   0.05352   0.04426  -0.0511   0.2127   1.0000
  11.500   1.4256   0.05329   0.04403  -0.0476   0.2027   1.0000
  11.750   1.4112   0.05483   0.04584  -0.0430   0.1955   1.0000
  12.000   1.4056   0.05532   0.04639  -0.0395   0.1865   1.0000
  12.250   1.3906   0.05757   0.04894  -0.0362   0.1801   1.0000
  12.500   1.3839   0.05878   0.05024  -0.0336   0.1722   1.0000
  12.750   1.3668   0.06232   0.05414  -0.0316   0.1675   1.0000
  13.000   1.3614   0.06419   0.05615  -0.0302   0.1608   1.0000
  13.250   1.3418   0.06882   0.06109  -0.0295   0.1571   1.0000
  13.500   1.3174   0.07466   0.06723  -0.0298   0.1547   1.0000
  13.750   1.2872   0.08214   0.07493  -0.0312   0.1542   1.0000
  14.000   1.2448   0.09287   0.08580  -0.0347   0.1568   1.0000
  14.250   1.2010   0.10559   0.09856  -0.0397   0.1606   1.0000
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