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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 50,000
Max Cl/Cd: 37.26 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa22-il-50000-n5.txt
Download as CSV file: xf-usa22-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 22 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3535   0.10966   0.10320  -0.0175   1.0000   0.0993
  -8.250  -0.3596   0.10803   0.10170  -0.0208   1.0000   0.1003
  -8.000  -0.3593   0.10502   0.09882  -0.0227   1.0000   0.1008
  -7.750  -0.3415   0.09964   0.09343  -0.0205   1.0000   0.1028
  -7.500  -0.3357   0.09636   0.09021  -0.0207   1.0000   0.1042
  -7.250  -0.3328   0.09328   0.08722  -0.0219   1.0000   0.1046
  -7.000  -0.3299   0.08601   0.07994  -0.0300   1.0000   0.0566
  -6.750  -0.3237   0.08252   0.07651  -0.0302   1.0000   0.0548
  -6.500  -0.3186   0.07896   0.07303  -0.0318   1.0000   0.0539
  -6.250  -0.3133   0.07537   0.06949  -0.0338   1.0000   0.0536
  -6.000  -0.3071   0.07168   0.06585  -0.0359   1.0000   0.0538
  -5.750  -0.2996   0.06789   0.06208  -0.0381   1.0000   0.0541
  -5.500  -0.2909   0.06398   0.05815  -0.0402   1.0000   0.0543
  -5.250  -0.2805   0.05993   0.05406  -0.0422   1.0000   0.0542
  -5.000  -0.2682   0.05573   0.04975  -0.0443   1.0000   0.0538
  -4.750  -0.2531   0.05119   0.04504  -0.0466   1.0000   0.0536
  -4.500  -0.2349   0.04641   0.03996  -0.0492   1.0000   0.0540
  -4.250  -0.1851   0.03902   0.03144  -0.0580   0.9906   0.0581
  -4.000  -0.1443   0.03547   0.02768  -0.0625   0.9794   0.0623
  -3.750  -0.0994   0.03181   0.02319  -0.0670   0.9680   0.0700
  -3.500  -0.0569   0.02900   0.01984  -0.0705   0.9559   0.0775
  -3.250  -0.0146   0.02702   0.01737  -0.0735   0.9431   0.0893
  -3.000   0.0281   0.02532   0.01526  -0.0761   0.9303   0.0982
  -2.750   0.0687   0.02407   0.01379  -0.0783   0.9164   0.1088
  -2.500   0.1077   0.02318   0.01268  -0.0800   0.9012   0.1251
  -2.250   0.1464   0.02227   0.01157  -0.0815   0.8853   0.1404
  -2.000   0.1826   0.02152   0.01080  -0.0826   0.8683   0.1719
  -1.750   0.2160   0.02100   0.01045  -0.0832   0.8501   0.2293
  -1.500   0.2464   0.02078   0.01017  -0.0831   0.8298   0.2918
  -1.250   0.2763   0.02046   0.00978  -0.0831   0.8108   0.3516
  -1.000   0.3040   0.01988   0.00931  -0.0827   0.7918   0.4182
  -0.750   0.3300   0.01914   0.00889  -0.0819   0.7727   0.4805
  -0.500   0.3644   0.01775   0.00847  -0.0817   0.7544   1.0000
  -0.250   0.3931   0.01791   0.00819  -0.0813   0.7367   1.0000
   0.000   0.4205   0.01811   0.00800  -0.0807   0.7189   1.0000
   0.250   0.4472   0.01835   0.00793  -0.0801   0.7014   1.0000
   0.500   0.4737   0.01861   0.00791  -0.0795   0.6848   1.0000
   0.750   0.5000   0.01888   0.00793  -0.0789   0.6688   1.0000
   1.000   0.5261   0.01918   0.00800  -0.0784   0.6537   1.0000
   1.250   0.5522   0.01948   0.00811  -0.0778   0.6392   1.0000
   1.500   0.5786   0.01980   0.00826  -0.0774   0.6253   1.0000
   1.750   0.6049   0.02013   0.00844  -0.0769   0.6121   1.0000
   2.000   0.6312   0.02046   0.00863  -0.0765   0.5993   1.0000
   2.250   0.6576   0.02079   0.00883  -0.0760   0.5873   1.0000
   2.500   0.6833   0.02116   0.00912  -0.0755   0.5744   1.0000
   2.750   0.7089   0.02154   0.00943  -0.0750   0.5618   1.0000
   3.000   0.7343   0.02192   0.00978  -0.0745   0.5495   1.0000
   3.250   0.7597   0.02230   0.01011  -0.0740   0.5376   1.0000
   3.500   0.7852   0.02268   0.01042  -0.0734   0.5261   1.0000
   3.750   0.8107   0.02305   0.01078  -0.0729   0.5148   1.0000
   4.000   0.8353   0.02351   0.01125  -0.0723   0.5025   1.0000
   4.250   0.8599   0.02396   0.01174  -0.0718   0.4907   1.0000
   4.500   0.8847   0.02442   0.01224  -0.0712   0.4795   1.0000
   4.750   0.9098   0.02485   0.01267  -0.0706   0.4689   1.0000
   5.000   0.9340   0.02537   0.01325  -0.0700   0.4574   1.0000
   5.250   0.9578   0.02593   0.01392  -0.0694   0.4458   1.0000
   5.500   0.9818   0.02650   0.01461  -0.0688   0.4351   1.0000
   5.750   1.0065   0.02701   0.01516  -0.0682   0.4252   1.0000
   6.000   1.0295   0.02767   0.01598  -0.0675   0.4138   1.0000
   6.250   1.0523   0.02839   0.01687  -0.0668   0.4030   1.0000
   6.500   1.0757   0.02904   0.01769  -0.0662   0.3930   1.0000
   6.750   1.0989   0.02970   0.01849  -0.0655   0.3831   1.0000
   7.000   1.1202   0.03060   0.01964  -0.0647   0.3727   1.0000
   7.250   1.1430   0.03138   0.02059  -0.0640   0.3641   1.0000
   7.500   1.1649   0.03222   0.02167  -0.0632   0.3549   1.0000
   7.750   1.1843   0.03292   0.02266  -0.0621   0.3427   1.0000
   8.000   1.2016   0.03268   0.02245  -0.0603   0.3226   1.0000
   8.250   1.2137   0.03290   0.02283  -0.0582   0.2988   1.0000
   8.500   1.2290   0.03340   0.02348  -0.0566   0.2821   1.0000
   8.750   1.2417   0.03410   0.02434  -0.0548   0.2628   1.0000
   9.000   1.2517   0.03497   0.02531  -0.0529   0.2402   1.0000
   9.250   1.2582   0.03619   0.02658  -0.0509   0.2137   1.0000
   9.500   1.2629   0.03775   0.02819  -0.0489   0.1869   1.0000
   9.750   1.2621   0.03973   0.03016  -0.0467   0.1544   1.0000
  10.000   1.2543   0.04253   0.03277  -0.0447   0.0952   1.0000
  10.250   1.2325   0.04718   0.03696  -0.0438   0.0620   1.0000
  10.500   1.2165   0.05194   0.04173  -0.0440   0.0503   1.0000
  10.750   1.2045   0.05667   0.04653  -0.0447   0.0463   1.0000
  11.000   1.1925   0.06169   0.05168  -0.0458   0.0437   1.0000
  11.250   1.1811   0.06683   0.05696  -0.0472   0.0420   1.0000
  11.500   1.1699   0.07211   0.06241  -0.0488   0.0405   1.0000
  11.750   1.1584   0.07752   0.06799  -0.0504   0.0394   1.0000
  12.000   1.1467   0.08302   0.07366  -0.0521   0.0384   1.0000
  12.250   1.1352   0.08857   0.07934  -0.0538   0.0375   1.0000
  12.500   1.1240   0.09409   0.08499  -0.0556   0.0367   1.0000
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