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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.97 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf6-il-1000000-n5.txt
Download as CSV file: xf-raf6-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1917   0.08979   0.08809  -0.0713   0.9847   0.0060
  -8.750  -0.1829   0.08612   0.08442  -0.0740   0.9824   0.0060
  -8.500  -0.1720   0.08222   0.08053  -0.0775   0.9807   0.0060
  -8.000  -0.1455   0.07543   0.07375  -0.0846   0.9782   0.0056
  -7.750  -0.1415   0.07203   0.07037  -0.0871   0.9721   0.0054
  -7.500  -0.1252   0.06714   0.06547  -0.0942   0.9691   0.0052
  -7.250  -0.1144   0.06280   0.06112  -0.0989   0.9626   0.0051
  -7.000  -0.0948   0.05782   0.05609  -0.1054   0.9586   0.0051
  -6.750  -0.0807   0.05342   0.05163  -0.1091   0.9501   0.0050
  -6.500  -0.0621   0.04879   0.04690  -0.1131   0.9417   0.0050
  -6.250  -0.0402   0.04447   0.04247  -0.1165   0.9323   0.0052
  -6.000  -0.0173   0.03996   0.03779  -0.1194   0.9189   0.0054
  -5.500   0.0066   0.01311   0.00875  -0.1190   0.8755   0.0059
  -5.250   0.0318   0.01166   0.00688  -0.1185   0.8580   0.0060
  -5.000   0.0570   0.01092   0.00592  -0.1180   0.8413   0.0064
  -4.750   0.0831   0.01069   0.00556  -0.1176   0.8270   0.0066
  -4.500   0.1091   0.01036   0.00510  -0.1172   0.8157   0.0069
  -4.250   0.1353   0.00991   0.00452  -0.1168   0.8071   0.0073
  -3.750   0.1875   0.00919   0.00355  -0.1160   0.7879   0.0080
  -3.500   0.2133   0.00887   0.00312  -0.1155   0.7763   0.0083
  -3.250   0.2392   0.00868   0.00286  -0.1150   0.7631   0.0088
  -3.000   0.2652   0.00855   0.00266  -0.1146   0.7492   0.0095
  -2.750   0.2919   0.00842   0.00246  -0.1143   0.7372   0.0103
  -2.500   0.3182   0.00824   0.00222  -0.1139   0.7240   0.0111
  -2.250   0.3439   0.00816   0.00206  -0.1134   0.7054   0.0120
  -2.000   0.3690   0.00813   0.00193  -0.1127   0.6812   0.0131
  -1.750   0.3932   0.00816   0.00181  -0.1119   0.6503   0.0146
  -1.500   0.4165   0.00828   0.00177  -0.1109   0.6090   0.0164
  -1.250   0.4390   0.00850   0.00176  -0.1098   0.5582   0.0180
  -1.000   0.4612   0.00875   0.00177  -0.1087   0.5002   0.0211
  -0.750   0.4844   0.00901   0.00181  -0.1078   0.4527   0.0241
  -0.500   0.5091   0.00916   0.00181  -0.1071   0.4221   0.0288
  -0.250   0.5347   0.00925   0.00183  -0.1067   0.4011   0.0358
   0.000   0.5604   0.00933   0.00185  -0.1063   0.3825   0.0471
   0.250   0.5862   0.00941   0.00188  -0.1059   0.3644   0.0633
   0.500   0.6089   0.00851   0.00202  -0.1057   0.3457   0.5146
   0.750   0.6266   0.00777   0.00219  -0.1037   0.3261   0.8636
   1.000   0.6607   0.00784   0.00233  -0.1049   0.3007   0.9928
   1.250   0.6917   0.00806   0.00240  -0.1058   0.2816   1.0000
   1.500   0.7158   0.00824   0.00248  -0.1050   0.2674   1.0000
   1.750   0.7404   0.00841   0.00256  -0.1044   0.2562   1.0000
   2.000   0.7651   0.00857   0.00264  -0.1038   0.2466   1.0000
   2.250   0.7898   0.00875   0.00274  -0.1033   0.2370   1.0000
   2.500   0.8151   0.00890   0.00284  -0.1028   0.2300   1.0000
   2.750   0.8403   0.00906   0.00294  -0.1023   0.2240   1.0000
   3.000   0.8657   0.00921   0.00305  -0.1019   0.2194   1.0000
   3.250   0.8912   0.00935   0.00316  -0.1015   0.2153   1.0000
   3.500   0.9164   0.00951   0.00328  -0.1011   0.2103   1.0000
   3.750   0.9414   0.00969   0.00342  -0.1006   0.2053   1.0000
   4.000   0.9671   0.00982   0.00355  -0.1003   0.2026   1.0000
   4.250   0.9924   0.00997   0.00369  -0.0999   0.1988   1.0000
   4.500   1.0174   0.01015   0.00383  -0.0994   0.1949   1.0000
   4.750   1.0421   0.01034   0.00400  -0.0990   0.1905   1.0000
   5.000   1.0672   0.01049   0.00416  -0.0986   0.1878   1.0000
   5.250   1.0923   0.01064   0.00432  -0.0981   0.1852   1.0000
   5.500   1.1170   0.01082   0.00449  -0.0977   0.1817   1.0000
   5.750   1.1412   0.01102   0.00468  -0.0971   0.1777   1.0000
   6.000   1.1653   0.01123   0.00488  -0.0966   0.1740   1.0000
   6.250   1.1898   0.01140   0.00507  -0.0961   0.1720   1.0000
   6.500   1.2140   0.01158   0.00527  -0.0955   0.1693   1.0000
   6.750   1.2376   0.01179   0.00549  -0.0949   0.1658   1.0000
   7.000   1.2605   0.01204   0.00573  -0.0942   0.1610   1.0000
   7.250   1.2831   0.01229   0.00596  -0.0934   0.1531   1.0000
   7.500   1.3040   0.01260   0.00623  -0.0923   0.1439   1.0000
   7.750   1.3241   0.01296   0.00653  -0.0910   0.1332   1.0000
   8.000   1.3444   0.01331   0.00686  -0.0898   0.1235   1.0000
   8.250   1.3629   0.01378   0.00726  -0.0883   0.1096   1.0000
   8.500   1.3798   0.01437   0.00774  -0.0866   0.0937   1.0000
   8.750   1.3949   0.01508   0.00834  -0.0846   0.0760   1.0000
   9.000   1.3964   0.01680   0.00975  -0.0804   0.0221   1.0000
   9.250   1.4109   0.01757   0.01050  -0.0784   0.0129   1.0000
   9.500   1.4277   0.01815   0.01110  -0.0767   0.0096   1.0000
   9.750   1.4446   0.01870   0.01168  -0.0752   0.0078   1.0000
  10.000   1.4610   0.01929   0.01230  -0.0735   0.0066   1.0000
  10.250   1.4774   0.01986   0.01293  -0.0720   0.0058   1.0000
  10.500   1.4925   0.02052   0.01363  -0.0702   0.0051   1.0000
  10.750   1.5081   0.02115   0.01431  -0.0686   0.0046   1.0000
  11.000   1.5226   0.02184   0.01505  -0.0669   0.0042   1.0000
  11.250   1.5356   0.02263   0.01590  -0.0650   0.0038   1.0000
  11.500   1.5492   0.02338   0.01672  -0.0632   0.0035   1.0000
  12.000   1.5734   0.02510   0.01859  -0.0595   0.0031   1.0000
  12.250   1.5836   0.02611   0.01967  -0.0575   0.0029   1.0000
  12.500   1.5918   0.02730   0.02093  -0.0554   0.0027   1.0000
  12.750   1.6010   0.02842   0.02214  -0.0535   0.0026   1.0000
  13.000   1.6091   0.02964   0.02346  -0.0517   0.0025   1.0000
  13.250   1.6164   0.03098   0.02488  -0.0498   0.0023   1.0000
  13.500   1.6228   0.03241   0.02640  -0.0481   0.0022   1.0000
  13.750   1.6282   0.03397   0.02805  -0.0464   0.0021   1.0000
  14.000   1.6321   0.03573   0.02989  -0.0448   0.0020   1.0000
  14.250   1.6340   0.03772   0.03197  -0.0432   0.0019   1.0000
  14.500   1.6322   0.04012   0.03449  -0.0415   0.0018   1.0000
  14.750   1.6301   0.04268   0.03716  -0.0402   0.0018   1.0000
  15.000   1.6283   0.04535   0.03994  -0.0391   0.0017   1.0000
  15.250   1.6248   0.04831   0.04305  -0.0383   0.0017   1.0000
  15.500   1.6192   0.05169   0.04655  -0.0377   0.0017   1.0000
  15.750   1.6115   0.05555   0.05054  -0.0376   0.0016   1.0000
  16.000   1.6018   0.05991   0.05504  -0.0379   0.0016   1.0000
  16.250   1.5886   0.06502   0.06029  -0.0387   0.0016   1.0000
  16.500   1.5729   0.07086   0.06629  -0.0402   0.0016   1.0000
  16.750   1.5538   0.07762   0.07321  -0.0424   0.0016   1.0000
  17.000   1.5308   0.08529   0.08105  -0.0452   0.0016   1.0000
  17.250   1.5029   0.09395   0.08988  -0.0484   0.0016   1.0000
  17.500   1.4737   0.10290   0.09899  -0.0519   0.0016   1.0000
  17.750   1.4421   0.11230   0.10855  -0.0556   0.0016   1.0000
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