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USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 48 AIRFOIL (usa48-il)
Reynolds number: 50,000
Max Cl/Cd: 30.63 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa48-il-50000-n5.txt
Download as CSV file: xf-usa48-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 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  -0.5132   0.08856   0.08129  -0.0642   1.0000   0.0588
 -11.250  -0.5386   0.08181   0.07455  -0.0674   1.0000   0.0586
 -11.000  -0.5636   0.07634   0.06906  -0.0693   1.0000   0.0582
 -10.750  -0.5913   0.07172   0.06440  -0.0700   1.0000   0.0579
 -10.500  -0.6194   0.06811   0.06076  -0.0690   1.0000   0.0576
 -10.250  -0.6489   0.06544   0.05803  -0.0658   1.0000   0.0574
 -10.000  -0.6748   0.06267   0.05514  -0.0622   1.0000   0.0574
  -9.750  -0.6950   0.05976   0.05204  -0.0589   1.0000   0.0576
  -9.500  -0.7117   0.05682   0.04884  -0.0554   1.0000   0.0579
  -9.250  -0.7233   0.05396   0.04565  -0.0521   1.0000   0.0584
  -9.000  -0.7291   0.05119   0.04257  -0.0491   1.0000   0.0591
  -8.750  -0.7234   0.04914   0.04052  -0.0470   1.0000   0.0607
  -8.500  -0.7186   0.04734   0.03862  -0.0447   1.0000   0.0628
  -8.250  -0.7143   0.04529   0.03631  -0.0423   1.0000   0.0647
  -8.000  -0.7083   0.04313   0.03376  -0.0399   1.0000   0.0666
  -7.750  -0.6986   0.04126   0.03166  -0.0378   1.0000   0.0684
  -7.500  -0.6874   0.04002   0.03043  -0.0359   1.0000   0.0711
  -7.250  -0.6760   0.03871   0.02895  -0.0339   1.0000   0.0742
  -7.000  -0.6632   0.03736   0.02736  -0.0319   1.0000   0.0771
  -6.750  -0.6429   0.03631   0.02630  -0.0316   0.9975   0.0808
  -6.500  -0.6091   0.03515   0.02479  -0.0334   0.9908   0.0867
  -6.250  -0.5760   0.03404   0.02366  -0.0352   0.9840   0.0918
  -6.000  -0.5437   0.03307   0.02246  -0.0365   0.9763   0.0991
  -5.750  -0.5139   0.03201   0.02136  -0.0377   0.9684   0.1064
  -5.500  -0.4820   0.03099   0.02022  -0.0391   0.9611   0.1150
  -5.250  -0.4554   0.02987   0.01919  -0.0398   0.9522   0.1300
  -5.000  -0.4289   0.02875   0.01845  -0.0406   0.9436   0.1598
  -4.750  -0.3974   0.02801   0.01793  -0.0420   0.9358   0.2331
  -4.500  -0.3718   0.02759   0.01760  -0.0423   0.9261   0.2900
  -4.250  -0.3371   0.02735   0.01735  -0.0440   0.9191   0.3420
  -4.000  -0.3130   0.02714   0.01708  -0.0437   0.9086   0.3737
  -3.750  -0.2807   0.02690   0.01677  -0.0448   0.9012   0.4039
  -3.500  -0.2547   0.02665   0.01654  -0.0447   0.8916   0.4345
  -3.250  -0.2266   0.02639   0.01636  -0.0448   0.8834   0.4700
  -3.000  -0.1989   0.02616   0.01625  -0.0447   0.8747   0.5040
  -2.750  -0.1738   0.02607   0.01636  -0.0438   0.8659   0.5423
  -2.500  -0.1460   0.02610   0.01659  -0.0430   0.8578   0.5875
  -2.250  -0.1239   0.02623   0.01669  -0.0416   0.8481   0.6320
  -2.000  -0.0930   0.02618   0.01651  -0.0418   0.8409   0.6741
  -1.750  -0.0723   0.02621   0.01646  -0.0403   0.8305   0.7063
  -1.500  -0.0389   0.02602   0.01617  -0.0407   0.8245   0.7379
  -1.250  -0.0187   0.02603   0.01614  -0.0390   0.8141   0.7655
  -1.000   0.0179   0.02579   0.01583  -0.0399   0.8086   0.7939
  -0.750   0.0429   0.02585   0.01589  -0.0390   0.7985   0.8195
  -0.500   0.0874   0.02569   0.01569  -0.0413   0.7933   0.8477
  -0.250   0.1264   0.02584   0.01582  -0.0431   0.7844   0.8752
   0.000   0.1871   0.02585   0.01575  -0.0488   0.7790   0.9018
   0.250   0.2437   0.02590   0.01571  -0.0540   0.7724   0.9263
   0.500   0.3015   0.02592   0.01565  -0.0597   0.7645   0.9453
   0.750   0.3614   0.02571   0.01533  -0.0656   0.7582   0.9600
   1.000   0.4092   0.02570   0.01526  -0.0698   0.7480   0.9755
   1.250   0.4598   0.02555   0.01504  -0.0744   0.7388   0.9899
   1.500   0.5044   0.02535   0.01478  -0.0778   0.7296   1.0000
   1.750   0.5106   0.02547   0.01486  -0.0745   0.7175   1.0000
   2.000   0.5322   0.02536   0.01469  -0.0736   0.7081   1.0000
   2.500   0.5556   0.02572   0.01495  -0.0686   0.6858   1.0000
   2.750   0.5887   0.02558   0.01473  -0.0694   0.6779   1.0000
   3.000   0.5952   0.02604   0.01517  -0.0660   0.6656   1.0000
   3.250   0.6134   0.02630   0.01540  -0.0645   0.6553   1.0000
   3.500   0.6416   0.02635   0.01541  -0.0644   0.6463   1.0000
   3.750   0.6537   0.02682   0.01589  -0.0619   0.6346   1.0000
   4.000   0.6778   0.02699   0.01603  -0.0612   0.6246   1.0000
   4.250   0.7039   0.02706   0.01609  -0.0607   0.6140   1.0000
   4.750   0.7389   0.02761   0.01667  -0.0570   0.5889   1.0000
   5.000   0.7643   0.02764   0.01668  -0.0562   0.5769   1.0000
   5.250   0.7910   0.02765   0.01669  -0.0556   0.5649   1.0000
   5.500   0.8053   0.02805   0.01712  -0.0534   0.5518   1.0000
   5.750   0.8226   0.02838   0.01748  -0.0515   0.5391   1.0000
   6.000   0.8441   0.02861   0.01773  -0.0503   0.5272   1.0000
   6.250   0.8712   0.02869   0.01782  -0.0499   0.5158   1.0000
   6.500   0.8820   0.02929   0.01850  -0.0472   0.5031   1.0000
   6.750   0.8969   0.02980   0.01907  -0.0452   0.4913   1.0000
   7.000   0.9172   0.03012   0.01943  -0.0439   0.4799   1.0000
   7.250   0.9344   0.03051   0.01990  -0.0421   0.4682   1.0000
   7.500   0.9421   0.03116   0.02064  -0.0391   0.4555   1.0000
   7.750   0.9529   0.03171   0.02125  -0.0365   0.4426   1.0000
   8.000   0.9665   0.03220   0.02179  -0.0343   0.4302   1.0000
   8.250   0.9846   0.03256   0.02220  -0.0327   0.4186   1.0000
   8.500   0.9912   0.03347   0.02324  -0.0300   0.4066   1.0000
   8.750   1.0015   0.03427   0.02413  -0.0277   0.3950   1.0000
   9.000   1.0164   0.03489   0.02482  -0.0260   0.3838   1.0000
   9.250   1.0321   0.03546   0.02545  -0.0244   0.3723   1.0000
   9.500   1.0386   0.03654   0.02668  -0.0220   0.3601   1.0000
   9.750   1.0482   0.03752   0.02775  -0.0200   0.3481   1.0000
  10.000   1.0600   0.03839   0.02869  -0.0182   0.3361   1.0000
  10.250   1.0752   0.03912   0.02944  -0.0167   0.3245   1.0000
  10.500   1.0797   0.04053   0.03098  -0.0146   0.3122   1.0000
  10.750   1.0862   0.04194   0.03251  -0.0128   0.3010   1.0000
  11.000   1.0963   0.04310   0.03375  -0.0112   0.2898   1.0000
  11.250   1.1040   0.04430   0.03497  -0.0095   0.2779   1.0000
  11.500   1.1002   0.04643   0.03725  -0.0076   0.2663   1.0000
  11.750   1.0997   0.04833   0.03922  -0.0059   0.2549   1.0000
  12.000   1.1003   0.05008   0.04099  -0.0044   0.2432   1.0000
  12.250   1.0966   0.05243   0.04344  -0.0032   0.2321   1.0000
  12.500   1.0921   0.05508   0.04621  -0.0023   0.2219   1.0000
  12.750   1.0926   0.05719   0.04835  -0.0015   0.2121   1.0000
  13.000   1.0874   0.06020   0.05156  -0.0011   0.2028   1.0000
  13.250   1.0834   0.06313   0.05461  -0.0008   0.1936   1.0000
  13.500   1.0806   0.06585   0.05735  -0.0005   0.1835   1.0000
  13.750   1.0720   0.06955   0.06117  -0.0008   0.1728   1.0000
  14.000   1.0635   0.07340   0.06513  -0.0013   0.1621   1.0000
  14.250   1.0563   0.07712   0.06888  -0.0019   0.1509   1.0000
  14.500   1.0493   0.08090   0.07262  -0.0025   0.1393   1.0000
  14.750   1.0428   0.08464   0.07626  -0.0032   0.1281   1.0000
  15.000   1.0332   0.08926   0.08099  -0.0044   0.1173   1.0000
  15.250   1.0232   0.09412   0.08595  -0.0058   0.1067   1.0000
  15.500   1.0140   0.09902   0.09092  -0.0073   0.0964   1.0000
  15.750   1.0036   0.10444   0.09651  -0.0092   0.0863   1.0000
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