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ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 13% AIRFOIL (arad13-il)
Reynolds number: 50,000
Max Cl/Cd: 31.78 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad13-il-50000-n5.txt
Download as CSV file: xf-arad13-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 13% 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4150   0.10049   0.09327  -0.0185   1.0000   0.0706
  -8.750  -0.4183   0.09582   0.08867  -0.0211   1.0000   0.0705
  -8.500  -0.4233   0.09121   0.08413  -0.0237   1.0000   0.0707
  -8.250  -0.4301   0.08628   0.07926  -0.0270   1.0000   0.0710
  -8.000  -0.4344   0.08083   0.07383  -0.0309   1.0000   0.0715
  -7.750  -0.4376   0.07512   0.06809  -0.0346   1.0000   0.0720
  -7.500  -0.4395   0.06914   0.06202  -0.0380   1.0000   0.0725
  -7.250  -0.4393   0.06299   0.05567  -0.0408   1.0000   0.0731
  -7.000  -0.4378   0.05626   0.04853  -0.0435   1.0000   0.0748
  -6.750  -0.4272   0.05240   0.04445  -0.0441   1.0000   0.0769
  -6.500  -0.4133   0.04998   0.04192  -0.0437   1.0000   0.0792
  -6.250  -0.4012   0.04622   0.03779  -0.0438   1.0000   0.0820
  -6.000  -0.3880   0.04268   0.03378  -0.0436   1.0000   0.0853
  -5.750  -0.3736   0.04155   0.03267  -0.0423   1.0000   0.0880
  -5.500  -0.3597   0.03947   0.03026  -0.0413   1.0000   0.0917
  -5.250  -0.3455   0.03753   0.02797  -0.0402   1.0000   0.0956
  -5.000  -0.3157   0.03629   0.02665  -0.0417   0.9940   0.1003
  -4.750  -0.2742   0.03414   0.02406  -0.0451   0.9836   0.1073
  -4.500  -0.2327   0.03274   0.02242  -0.0482   0.9725   0.1150
  -4.250  -0.1911   0.03140   0.02093  -0.0513   0.9616   0.1226
  -4.000  -0.1464   0.03004   0.01923  -0.0546   0.9521   0.1325
  -3.750  -0.1062   0.02911   0.01827  -0.0571   0.9397   0.1421
  -3.500  -0.0671   0.02818   0.01726  -0.0592   0.9267   0.1526
  -3.250  -0.0275   0.02734   0.01627  -0.0612   0.9142   0.1652
  -3.000   0.0114   0.02664   0.01546  -0.0630   0.9015   0.1794
  -2.750   0.0450   0.02604   0.01489  -0.0637   0.8860   0.1935
  -2.500   0.0782   0.02550   0.01433  -0.0643   0.8708   0.2096
  -2.250   0.1103   0.02500   0.01381  -0.0646   0.8556   0.2281
  -2.000   0.1413   0.02451   0.01333  -0.0646   0.8408   0.2496
  -1.750   0.1705   0.02404   0.01290  -0.0643   0.8253   0.2754
  -1.500   0.1974   0.02354   0.01257  -0.0637   0.8085   0.3090
  -1.250   0.2231   0.02290   0.01231  -0.0629   0.7918   0.3702
  -1.000   0.2405   0.02156   0.01224  -0.0599   0.7762   0.6171
  -0.750   0.2861   0.02085   0.01192  -0.0608   0.7576   1.0000
  -0.500   0.3119   0.02096   0.01171  -0.0598   0.7404   1.0000
  -0.250   0.3376   0.02108   0.01153  -0.0587   0.7235   1.0000
   0.000   0.3634   0.02120   0.01139  -0.0577   0.7066   1.0000
   0.250   0.3893   0.02132   0.01128  -0.0568   0.6898   1.0000
   0.500   0.4151   0.02149   0.01124  -0.0559   0.6720   1.0000
   0.750   0.4409   0.02167   0.01123  -0.0551   0.6541   1.0000
   1.000   0.4669   0.02186   0.01123  -0.0543   0.6362   1.0000
   1.250   0.4930   0.02206   0.01126  -0.0536   0.6182   1.0000
   1.500   0.5192   0.02227   0.01130  -0.0529   0.5999   1.0000
   1.750   0.5455   0.02249   0.01137  -0.0522   0.5815   1.0000
   2.000   0.5718   0.02273   0.01146  -0.0516   0.5628   1.0000
   2.250   0.5979   0.02299   0.01157  -0.0509   0.5441   1.0000
   2.500   0.6240   0.02327   0.01171  -0.0503   0.5252   1.0000
   2.750   0.6500   0.02358   0.01187  -0.0497   0.5063   1.0000
   3.000   0.6759   0.02392   0.01207  -0.0492   0.4875   1.0000
   3.250   0.7017   0.02429   0.01231  -0.0486   0.4691   1.0000
   3.500   0.7273   0.02470   0.01260  -0.0481   0.4509   1.0000
   3.750   0.7528   0.02514   0.01292  -0.0476   0.4333   1.0000
   4.000   0.7782   0.02563   0.01330  -0.0471   0.4166   1.0000
   4.250   0.8034   0.02616   0.01373  -0.0467   0.4006   1.0000
   4.500   0.8284   0.02671   0.01418  -0.0462   0.3856   1.0000
   4.750   0.8535   0.02729   0.01464  -0.0457   0.3722   1.0000
   5.000   0.8784   0.02789   0.01514  -0.0453   0.3595   1.0000
   5.250   0.9028   0.02858   0.01581  -0.0449   0.3466   1.0000
   5.500   0.9273   0.02927   0.01642  -0.0444   0.3356   1.0000
   5.750   0.9518   0.02996   0.01704  -0.0440   0.3254   1.0000
   6.000   0.9757   0.03077   0.01788  -0.0436   0.3151   1.0000
   6.250   1.0002   0.03147   0.01844  -0.0431   0.3067   1.0000
   6.500   1.0231   0.03240   0.01949  -0.0427   0.2973   1.0000
   6.750   1.0475   0.03316   0.02013  -0.0423   0.2900   1.0000
   7.000   1.0695   0.03418   0.02127  -0.0418   0.2817   1.0000
   7.250   1.0928   0.03503   0.02210  -0.0413   0.2746   1.0000
   7.500   1.1150   0.03607   0.02319  -0.0408   0.2680   1.0000
   7.750   1.1359   0.03716   0.02438  -0.0402   0.2611   1.0000
   8.000   1.1600   0.03798   0.02511  -0.0398   0.2556   1.0000
   8.250   1.1776   0.03939   0.02674  -0.0390   0.2492   1.0000
   8.500   1.1973   0.04056   0.02800  -0.0383   0.2434   1.0000
   8.750   1.2214   0.04143   0.02876  -0.0379   0.2388   1.0000
   9.000   1.2339   0.04318   0.03083  -0.0367   0.2330   1.0000
   9.250   1.2500   0.04461   0.03239  -0.0357   0.2279   1.0000
   9.500   1.2714   0.04563   0.03338  -0.0352   0.2237   1.0000
   9.750   1.2831   0.04743   0.03539  -0.0339   0.2192   1.0000
  10.000   1.2891   0.04955   0.03777  -0.0323   0.2145   1.0000
  10.250   1.3020   0.05110   0.03942  -0.0311   0.2104   1.0000
  10.500   1.3244   0.05206   0.04032  -0.0306   0.2070   1.0000
  10.750   1.3177   0.05500   0.04360  -0.0282   0.2035   1.0000
  11.000   1.3015   0.05835   0.04727  -0.0253   0.2001   1.0000
  11.250   1.2870   0.06159   0.05072  -0.0228   0.1972   1.0000
  11.500   1.2882   0.06395   0.05316  -0.0215   0.1942   1.0000
  11.750   1.3197   0.06412   0.05322  -0.0212   0.1912   1.0000
  12.000   1.2498   0.07328   0.06284  -0.0204   0.1894   1.0000
  12.250   0.9906   0.12053   0.11066  -0.0435   0.1792   1.0000
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