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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.13 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa22-il-1000000.txt
Download as CSV file: xf-usa22-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3178   0.12496   0.12344  -0.0101   1.0000   0.0095
 -11.500  -0.3134   0.12209   0.12058  -0.0107   1.0000   0.0096
  -7.750  -0.4633   0.02184   0.01904  -0.0700   0.9932   0.0089
  -7.500  -0.4324   0.01965   0.01652  -0.0719   0.9889   0.0091
  -7.250  -0.4043   0.01492   0.01106  -0.0744   0.9845   0.0098
  -7.000  -0.3735   0.01403   0.01005  -0.0753   0.9778   0.0102
  -6.750  -0.3405   0.01328   0.00918  -0.0765   0.9709   0.0106
  -6.500  -0.3101   0.01251   0.00827  -0.0771   0.9602   0.0111
  -6.250  -0.2802   0.01181   0.00742  -0.0775   0.9472   0.0117
  -6.000  -0.2520   0.01127   0.00673  -0.0774   0.9310   0.0122
  -5.750  -0.2258   0.01061   0.00587  -0.0769   0.9136   0.0127
  -5.500  -0.2000   0.00997   0.00509  -0.0763   0.8964   0.0140
  -5.250  -0.1733   0.00977   0.00481  -0.0759   0.8788   0.0151
  -5.000  -0.1466   0.00951   0.00444  -0.0754   0.8592   0.0162
  -4.750  -0.1201   0.00920   0.00396  -0.0749   0.8357   0.0172
  -4.500  -0.0939   0.00885   0.00349  -0.0744   0.8063   0.0194
  -4.250  -0.0673   0.00879   0.00329  -0.0739   0.7747   0.0214
  -4.000  -0.0406   0.00860   0.00295  -0.0734   0.7477   0.0241
  -3.500   0.0142   0.00865   0.00283  -0.0729   0.7036   0.0295
  -3.250   0.0415   0.00838   0.00248  -0.0727   0.6851   0.0338
  -3.000   0.0691   0.00838   0.00242  -0.0725   0.6672   0.0368
  -2.750   0.0969   0.00841   0.00236  -0.0723   0.6490   0.0388
  -2.500   0.1244   0.00819   0.00203  -0.0721   0.6306   0.0423
  -2.250   0.1520   0.00811   0.00189  -0.0719   0.6116   0.0461
  -2.000   0.1796   0.00809   0.00177  -0.0717   0.5917   0.0491
  -1.750   0.2073   0.00809   0.00169  -0.0716   0.5716   0.0510
  -1.500   0.2348   0.00797   0.00147  -0.0714   0.5513   0.0575
  -1.250   0.2624   0.00794   0.00136  -0.0712   0.5317   0.0628
  -1.000   0.2900   0.00789   0.00125  -0.0710   0.5129   0.0746
  -0.750   0.3169   0.00765   0.00119  -0.0709   0.4953   0.1548
  -0.500   0.3442   0.00757   0.00119  -0.0708   0.4783   0.2074
  -0.250   0.3718   0.00757   0.00122  -0.0707   0.4636   0.2440
   0.000   0.3996   0.00761   0.00124  -0.0706   0.4521   0.2656
   0.250   0.4275   0.00766   0.00127  -0.0705   0.4433   0.2816
   0.750   0.4834   0.00774   0.00133  -0.0704   0.4277   0.3069
   1.000   0.5114   0.00777   0.00136  -0.0703   0.4200   0.3187
   1.250   0.5393   0.00781   0.00139  -0.0703   0.4136   0.3301
   1.500   0.5673   0.00784   0.00143  -0.0702   0.4074   0.3433
   1.750   0.5950   0.00788   0.00148  -0.0702   0.4012   0.3603
   2.000   0.6229   0.00784   0.00153  -0.0702   0.3957   0.3893
   2.250   0.6529   0.00652   0.00166  -0.0709   0.3895   1.0000
   2.500   0.6806   0.00661   0.00171  -0.0707   0.3839   1.0000
   2.750   0.7082   0.00671   0.00177  -0.0706   0.3774   1.0000
   3.000   0.7356   0.00682   0.00184  -0.0705   0.3708   1.0000
   3.250   0.7632   0.00691   0.00191  -0.0704   0.3640   1.0000
   3.500   0.7906   0.00704   0.00200  -0.0702   0.3573   1.0000
   3.750   0.8182   0.00713   0.00208  -0.0701   0.3505   1.0000
   4.000   0.8454   0.00727   0.00219  -0.0700   0.3430   1.0000
   4.250   0.8727   0.00740   0.00228  -0.0699   0.3320   1.0000
   4.500   0.8998   0.00756   0.00239  -0.0698   0.3191   1.0000
   4.750   0.9264   0.00778   0.00252  -0.0696   0.3016   1.0000
   5.000   0.9530   0.00800   0.00268  -0.0694   0.2842   1.0000
   5.250   0.9792   0.00826   0.00286  -0.0691   0.2647   1.0000
   5.500   1.0048   0.00860   0.00308  -0.0689   0.2423   1.0000
   5.750   1.0301   0.00898   0.00333  -0.0685   0.2189   1.0000
   6.000   1.0553   0.00937   0.00362  -0.0682   0.1958   1.0000
   6.250   1.0792   0.00994   0.00398  -0.0677   0.1633   1.0000
   6.500   1.0919   0.01205   0.00532  -0.0659   0.0323   1.0000
   6.750   1.1157   0.01262   0.00586  -0.0654   0.0169   1.0000
   7.000   1.1403   0.01307   0.00635  -0.0649   0.0145   1.0000
   7.250   1.1642   0.01360   0.00696  -0.0643   0.0129   1.0000
   7.500   1.1887   0.01401   0.00742  -0.0638   0.0122   1.0000
   7.750   1.2126   0.01449   0.00794  -0.0633   0.0114   1.0000
   8.000   1.2360   0.01500   0.00850  -0.0627   0.0105   1.0000
   8.250   1.2580   0.01568   0.00924  -0.0619   0.0097   1.0000
   8.500   1.2746   0.01698   0.01070  -0.0604   0.0090   1.0000
   8.750   1.2972   0.01748   0.01125  -0.0597   0.0087   1.0000
   9.000   1.3181   0.01815   0.01198  -0.0589   0.0084   1.0000
   9.250   1.3376   0.01892   0.01283  -0.0578   0.0080   1.0000
   9.500   1.3559   0.01976   0.01374  -0.0567   0.0077   1.0000
   9.750   1.3731   0.02065   0.01469  -0.0554   0.0074   1.0000
  10.000   1.3898   0.02150   0.01560  -0.0541   0.0070   1.0000
  10.250   1.4047   0.02244   0.01659  -0.0527   0.0067   1.0000
  10.500   1.4106   0.02393   0.01816  -0.0501   0.0064   1.0000
  10.750   1.3961   0.02649   0.02085  -0.0452   0.0061   1.0000
  11.000   1.3987   0.02812   0.02257  -0.0430   0.0060   1.0000
  11.250   1.4059   0.02955   0.02410  -0.0415   0.0059   1.0000
  11.500   1.4102   0.03137   0.02601  -0.0402   0.0058   1.0000
  11.750   1.4134   0.03347   0.02821  -0.0393   0.0057   1.0000
  12.000   1.4151   0.03590   0.03073  -0.0386   0.0056   1.0000
  12.250   1.4159   0.03860   0.03354  -0.0383   0.0055   1.0000
  12.500   1.4160   0.04148   0.03652  -0.0381   0.0055   1.0000
  12.750   1.4158   0.04449   0.03962  -0.0381   0.0054   1.0000
  13.000   1.4151   0.04759   0.04282  -0.0381   0.0053   1.0000
  13.250   1.4135   0.05080   0.04613  -0.0382   0.0052   1.0000
  13.500   1.4119   0.05408   0.04950  -0.0383   0.0051   1.0000
  13.750   1.4096   0.05744   0.05296  -0.0385   0.0050   1.0000
  14.000   1.4071   0.06091   0.05652  -0.0389   0.0050   1.0000
  14.250   1.4038   0.06449   0.06020  -0.0394   0.0049   1.0000
  14.500   1.4001   0.06819   0.06401  -0.0399   0.0048   1.0000
  14.750   1.3966   0.07206   0.06797  -0.0409   0.0047   1.0000
  15.000   1.3920   0.07604   0.07205  -0.0417   0.0047   1.0000
  15.250   1.3877   0.08018   0.07627  -0.0431   0.0046   1.0000
  15.500   1.3820   0.08450   0.08070  -0.0442   0.0046   1.0000
  15.750   1.3761   0.08903   0.08533  -0.0457   0.0045   1.0000
  16.000   1.3696   0.09371   0.09011  -0.0473   0.0044   1.0000
  16.250   1.3626   0.09855   0.09505  -0.0490   0.0044   1.0000
  16.500   1.3556   0.10353   0.10013  -0.0510   0.0044   1.0000
  16.750   1.3475   0.10870   0.10541  -0.0530   0.0043   1.0000
  17.000   1.3386   0.11407   0.11089  -0.0552   0.0043   1.0000
  17.250   1.3284   0.11981   0.11675  -0.0576   0.0043   1.0000
  17.500   1.3192   0.12556   0.12260  -0.0603   0.0042   1.0000
  17.750   1.3094   0.13156   0.12872  -0.0633   0.0042   1.0000
  18.000   1.2981   0.13799   0.13528  -0.0666   0.0042   1.0000
  18.250   1.2879   0.14437   0.14176  -0.0701   0.0042   1.0000
  18.500   1.2766   0.15128   0.14879  -0.0740   0.0042   1.0000
  18.750   1.2650   0.15850   0.15613  -0.0783   0.0042   1.0000
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