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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 50,000
Max Cl/Cd: 25.79 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf48-il-50000-n5.txt
Download as CSV file: xf-raf48-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF-48 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4049   0.10372   0.09603  -0.0471   1.0000   0.0857
 -11.250  -0.4144   0.09832   0.09070  -0.0495   1.0000   0.0865
 -11.000  -0.4292   0.09204   0.08449  -0.0526   1.0000   0.0872
 -10.750  -0.4520   0.08419   0.07675  -0.0569   1.0000   0.0874
 -10.500  -0.4916   0.07419   0.06680  -0.0633   1.0000   0.0869
 -10.250  -0.5348   0.06739   0.06002  -0.0659   1.0000   0.0863
 -10.000  -0.5754   0.06338   0.05602  -0.0635   1.0000   0.0858
  -9.750  -0.6114   0.06048   0.05311  -0.0592   1.0000   0.0857
  -9.500  -0.6425   0.05806   0.05064  -0.0543   1.0000   0.0857
  -9.250  -0.6707   0.05597   0.04843  -0.0490   1.0000   0.0860
  -9.000  -0.6941   0.05386   0.04614  -0.0440   1.0000   0.0865
  -8.750  -0.7003   0.05042   0.04228  -0.0424   0.9941   0.0878
  -8.500  -0.6876   0.04659   0.03784  -0.0436   0.9832   0.0903
  -8.250  -0.6617   0.04511   0.03634  -0.0448   0.9743   0.0934
  -8.000  -0.6399   0.04304   0.03397  -0.0456   0.9653   0.0971
  -7.750  -0.6168   0.04041   0.03079  -0.0466   0.9573   0.1009
  -7.500  -0.5938   0.03884   0.02904  -0.0469   0.9483   0.1048
  -7.250  -0.5626   0.03750   0.02755  -0.0485   0.9420   0.1103
  -7.000  -0.5409   0.03590   0.02548  -0.0482   0.9330   0.1159
  -6.750  -0.5078   0.03482   0.02445  -0.0498   0.9272   0.1223
  -6.500  -0.4832   0.03368   0.02298  -0.0497   0.9189   0.1304
  -6.250  -0.4515   0.03274   0.02208  -0.0510   0.9127   0.1389
  -6.000  -0.4209   0.03177   0.02098  -0.0519   0.9063   0.1499
  -5.750  -0.3932   0.03102   0.02005  -0.0522   0.8986   0.1627
  -5.500  -0.3570   0.03019   0.01917  -0.0540   0.8936   0.1782
  -5.250  -0.3359   0.02970   0.01872  -0.0531   0.8844   0.1922
  -5.000  -0.3023   0.02906   0.01799  -0.0543   0.8784   0.2117
  -4.750  -0.2794   0.02865   0.01761  -0.0537   0.8696   0.2298
  -4.500  -0.2485   0.02810   0.01712  -0.0544   0.8626   0.2524
  -4.250  -0.2237   0.02769   0.01671  -0.0540   0.8539   0.2759
  -4.000  -0.1936   0.02714   0.01622  -0.0544   0.8462   0.3036
  -3.750  -0.1688   0.02670   0.01583  -0.0540   0.8375   0.3333
  -3.500  -0.1413   0.02618   0.01545  -0.0538   0.8295   0.3693
  -3.250  -0.1196   0.02577   0.01525  -0.0527   0.8208   0.4103
  -3.000  -0.0964   0.02534   0.01505  -0.0515   0.8126   0.4650
  -2.750  -0.0752   0.02500   0.01500  -0.0499   0.8045   0.5302
  -2.250  -0.0136   0.02458   0.01514  -0.0485   0.7908   0.6961
  -2.000   0.0149   0.02480   0.01544  -0.0477   0.7812   0.7612
  -1.750   0.0654   0.02486   0.01542  -0.0503   0.7758   0.8197
  -1.500   0.1056   0.02517   0.01563  -0.0519   0.7672   0.8644
  -1.250   0.1694   0.02530   0.01557  -0.0574   0.7608   0.8990
  -1.000   0.2370   0.02536   0.01542  -0.0640   0.7547   0.9239
  -0.750   0.2877   0.02551   0.01543  -0.0683   0.7454   0.9474
  -0.500   0.3469   0.02531   0.01504  -0.0739   0.7394   0.9684
  -0.250   0.4023   0.02534   0.01497  -0.0798   0.7290   0.9911
   0.000   0.4440   0.02507   0.01456  -0.0827   0.7221   1.0000
   0.250   0.4527   0.02538   0.01483  -0.0801   0.7107   1.0000
   0.500   0.4742   0.02528   0.01460  -0.0790   0.7038   1.0000
   0.750   0.4814   0.02571   0.01500  -0.0762   0.6922   1.0000
   1.000   0.5015   0.02572   0.01492  -0.0748   0.6851   1.0000
   1.250   0.5100   0.02616   0.01533  -0.0720   0.6742   1.0000
   1.500   0.5288   0.02628   0.01537  -0.0704   0.6667   1.0000
   1.750   0.5390   0.02673   0.01579  -0.0678   0.6566   1.0000
   2.000   0.5582   0.02690   0.01589  -0.0663   0.6493   1.0000
   2.250   0.5685   0.02741   0.01639  -0.0637   0.6394   1.0000
   2.500   0.5894   0.02756   0.01647  -0.0624   0.6325   1.0000
   2.750   0.5986   0.02819   0.01709  -0.0597   0.6226   1.0000
   3.000   0.6251   0.02817   0.01701  -0.0590   0.6171   1.0000
   3.250   0.6293   0.02905   0.01791  -0.0557   0.6062   1.0000
   3.500   0.6571   0.02900   0.01780  -0.0552   0.6009   1.0000
   3.750   0.6599   0.03001   0.01884  -0.0519   0.5902   1.0000
   4.000   0.6880   0.02996   0.01875  -0.0514   0.5847   1.0000
   4.250   0.6910   0.03100   0.01983  -0.0480   0.5743   1.0000
   4.500   0.7190   0.03095   0.01975  -0.0475   0.5686   1.0000
   4.750   0.7224   0.03200   0.02084  -0.0443   0.5584   1.0000
   5.000   0.7510   0.03190   0.02074  -0.0438   0.5524   1.0000
   5.250   0.7542   0.03296   0.02184  -0.0405   0.5421   1.0000
   5.500   0.7847   0.03274   0.02163  -0.0402   0.5359   1.0000
   5.750   0.7865   0.03387   0.02280  -0.0368   0.5254   1.0000
   6.000   0.8198   0.03350   0.02244  -0.0368   0.5192   1.0000
   6.250   0.8192   0.03475   0.02374  -0.0332   0.5084   1.0000
   6.500   0.8570   0.03414   0.02316  -0.0335   0.5022   1.0000
   6.750   0.8531   0.03556   0.02464  -0.0297   0.4910   1.0000
   7.000   0.8891   0.03501   0.02411  -0.0298   0.4840   1.0000
   7.250   0.8882   0.03628   0.02546  -0.0263   0.4732   1.0000
   7.500   0.9072   0.03658   0.02582  -0.0248   0.4643   1.0000
   7.750   0.9250   0.03690   0.02619  -0.0231   0.4549   1.0000
   8.000   0.9274   0.03796   0.02731  -0.0200   0.4448   1.0000
   8.250   0.9641   0.03739   0.02679  -0.0201   0.4362   1.0000
   8.500   0.9520   0.03920   0.02867  -0.0157   0.4249   1.0000
   8.750   0.9857   0.03874   0.02825  -0.0155   0.4162   1.0000
   9.000   0.9825   0.04019   0.02978  -0.0123   0.4050   1.0000
   9.250   0.9830   0.04162   0.03129  -0.0097   0.3941   1.0000
   9.500   1.0176   0.04097   0.03069  -0.0093   0.3851   1.0000
   9.750   0.9993   0.04373   0.03356  -0.0060   0.3729   1.0000
  10.000   1.0052   0.04502   0.03492  -0.0042   0.3624   1.0000
  10.250   1.0281   0.04501   0.03497  -0.0031   0.3527   1.0000
  10.500   1.0105   0.04833   0.03840  -0.0009   0.3409   1.0000
  10.750   1.0205   0.04947   0.03962   0.0004   0.3312   1.0000
  11.000   1.0339   0.05024   0.04046   0.0016   0.3214   1.0000
  11.250   1.0169   0.05412   0.04444   0.0028   0.3103   1.0000
  11.500   1.0439   0.05360   0.04396   0.0040   0.3022   1.0000
  11.750   1.0337   0.05694   0.04741   0.0048   0.2918   1.0000
  12.000   1.0266   0.06019   0.05074   0.0054   0.2822   1.0000
  12.250   1.0586   0.05890   0.04950   0.0069   0.2740   1.0000
  12.500   1.0300   0.06479   0.05550   0.0067   0.2637   1.0000
  12.750   1.0475   0.06484   0.05557   0.0079   0.2537   1.0000
  13.000   1.0752   0.06337   0.05402   0.0095   0.2418   1.0000
  13.250   1.0409   0.07038   0.06122   0.0085   0.2325   1.0000
  13.500   1.0490   0.07162   0.06247   0.0092   0.2222   1.0000
  13.750   1.0715   0.07077   0.06154   0.0107   0.2110   1.0000
  14.250   1.0512   0.07902   0.07000   0.0096   0.1934   1.0000
  14.500   1.0346   0.08446   0.07557   0.0083   0.1849   1.0000
  14.750   1.0291   0.08823   0.07941   0.0077   0.1763   1.0000
  15.000   1.0450   0.08838   0.07953   0.0086   0.1668   1.0000
  15.250   1.0063   0.09828   0.08964   0.0049   0.1598   1.0000
  15.500   1.0308   0.09681   0.08808   0.0065   0.1506   1.0000
  15.750   0.9797   0.10968   0.10119   0.0010   0.1438   1.0000
  16.000   1.0062   0.10772   0.09917   0.0029   0.1359   1.0000
  16.250   0.9446   0.12376   0.11537  -0.0046   0.1290   1.0000
  16.500   0.9849   0.11866   0.11023  -0.0012   0.1227   1.0000
  16.750   0.9070   0.13990   0.13153  -0.0117   0.1156   1.0000
  17.000   0.9495   0.13360   0.12529  -0.0078   0.1114   1.0000
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