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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 500,000
Max Cl/Cd: 99.94 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa22-il-500000.txt
Download as CSV file: xf-usa22-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2809   0.09367   0.09164  -0.0193   1.0000   0.0215
  -9.000  -0.2836   0.08961   0.08760  -0.0220   1.0000   0.0221
  -8.750  -0.2824   0.08573   0.08375  -0.0235   1.0000   0.0222
  -8.500  -0.2809   0.08182   0.07985  -0.0249   1.0000   0.0223
  -8.250  -0.2800   0.07783   0.07589  -0.0262   1.0000   0.0223
  -8.000  -0.2801   0.07382   0.07190  -0.0275   1.0000   0.0224
  -7.750  -0.2815   0.06984   0.06795  -0.0288   1.0000   0.0224
  -7.500  -0.2953   0.06409   0.06226  -0.0289   1.0000   0.0230
  -7.250  -0.3013   0.06147   0.05970  -0.0279   1.0000   0.0232
  -7.000  -0.3000   0.05840   0.05666  -0.0287   0.9986   0.0235
  -6.750  -0.2803   0.05370   0.05195  -0.0344   0.9930   0.0240
  -6.500  -0.2594   0.04843   0.04665  -0.0411   0.9855   0.0248
  -6.250  -0.2976   0.03097   0.02818  -0.0672   0.9865   0.0166
  -6.000  -0.2678   0.02147   0.01759  -0.0729   0.9796   0.0167
  -5.750  -0.2366   0.01745   0.01298  -0.0752   0.9728   0.0179
  -5.500  -0.2033   0.01696   0.01241  -0.0765   0.9645   0.0192
  -5.250  -0.1697   0.01541   0.01057  -0.0777   0.9557   0.0204
  -5.000  -0.1385   0.01418   0.00907  -0.0782   0.9430   0.0217
  -4.750  -0.1094   0.01267   0.00727  -0.0783   0.9280   0.0233
  -4.500  -0.0816   0.01230   0.00684  -0.0781   0.9105   0.0254
  -4.250  -0.0546   0.01211   0.00654  -0.0775   0.8916   0.0279
  -4.000  -0.0280   0.01182   0.00608  -0.0768   0.8710   0.0299
  -3.750  -0.0027   0.01096   0.00510  -0.0762   0.8479   0.0337
  -3.500   0.0238   0.01089   0.00489  -0.0755   0.8218   0.0375
  -3.250   0.0495   0.01039   0.00421  -0.0748   0.7944   0.0416
  -3.000   0.0756   0.01017   0.00386  -0.0742   0.7670   0.0456
  -2.750   0.1023   0.01011   0.00364  -0.0737   0.7415   0.0496
  -2.500   0.1287   0.00982   0.00319  -0.0733   0.7192   0.0532
  -2.250   0.1553   0.00956   0.00284  -0.0729   0.6985   0.0584
  -2.000   0.1823   0.00945   0.00259  -0.0725   0.6787   0.0626
  -1.750   0.2094   0.00928   0.00231  -0.0722   0.6585   0.0676
  -1.500   0.2364   0.00912   0.00208  -0.0718   0.6385   0.0754
  -1.000   0.2897   0.00860   0.00184  -0.0713   0.5976   0.2016
  -0.750   0.3167   0.00862   0.00186  -0.0711   0.5774   0.2503
  -0.500   0.3440   0.00868   0.00187  -0.0708   0.5576   0.2753
  -0.250   0.3713   0.00877   0.00187  -0.0706   0.5390   0.2941
   0.000   0.3986   0.00884   0.00189  -0.0704   0.5218   0.3122
   0.250   0.4258   0.00891   0.00189  -0.0702   0.5060   0.3272
   0.500   0.4532   0.00897   0.00190  -0.0701   0.4917   0.3405
   0.750   0.4805   0.00901   0.00192  -0.0699   0.4794   0.3582
   1.000   0.5079   0.00903   0.00194  -0.0698   0.4693   0.3776
   1.500   0.5670   0.00765   0.00205  -0.0705   0.4519   1.0000
   1.750   0.5942   0.00780   0.00210  -0.0703   0.4440   1.0000
   2.000   0.6215   0.00791   0.00215  -0.0701   0.4359   1.0000
   2.250   0.6486   0.00806   0.00223  -0.0699   0.4288   1.0000
   2.500   0.6760   0.00818   0.00231  -0.0697   0.4216   1.0000
   2.750   0.7030   0.00834   0.00240  -0.0695   0.4151   1.0000
   3.000   0.7304   0.00845   0.00249  -0.0694   0.4081   1.0000
   3.250   0.7573   0.00862   0.00261  -0.0691   0.4015   1.0000
   3.500   0.7848   0.00872   0.00272  -0.0690   0.3945   1.0000
   4.000   0.8390   0.00900   0.00297  -0.0687   0.3796   1.0000
   4.250   0.8657   0.00918   0.00310  -0.0685   0.3719   1.0000
   4.500   0.8930   0.00929   0.00324  -0.0683   0.3636   1.0000
   4.750   0.9198   0.00945   0.00338  -0.0681   0.3544   1.0000
   5.000   0.9465   0.00961   0.00352  -0.0679   0.3407   1.0000
   5.250   0.9730   0.00979   0.00366  -0.0677   0.3257   1.0000
   5.500   0.9994   0.01000   0.00383  -0.0675   0.3098   1.0000
   5.750   1.0253   0.01026   0.00403  -0.0672   0.2917   1.0000
   6.000   1.0507   0.01058   0.00428  -0.0669   0.2730   1.0000
   6.250   1.0754   0.01098   0.00457  -0.0665   0.2467   1.0000
   6.500   1.0993   0.01150   0.00492  -0.0661   0.2180   1.0000
   6.750   1.1225   0.01210   0.00535  -0.0655   0.1838   1.0000
   7.000   1.1380   0.01373   0.00633  -0.0642   0.0871   1.0000
   7.250   1.1531   0.01540   0.00767  -0.0626   0.0225   1.0000
   7.500   1.1757   0.01608   0.00845  -0.0618   0.0186   1.0000
   7.750   1.1986   0.01666   0.00914  -0.0611   0.0176   1.0000
   8.000   1.2205   0.01735   0.00994  -0.0602   0.0166   1.0000
   8.250   1.2411   0.01817   0.01087  -0.0592   0.0157   1.0000
   8.500   1.2599   0.01912   0.01191  -0.0581   0.0147   1.0000
   8.750   1.2742   0.02049   0.01340  -0.0564   0.0136   1.0000
   9.000   1.2804   0.02249   0.01557  -0.0538   0.0129   1.0000
   9.250   1.2968   0.02339   0.01656  -0.0524   0.0127   1.0000
   9.500   1.3099   0.02452   0.01778  -0.0506   0.0124   1.0000
   9.750   1.3193   0.02579   0.01916  -0.0484   0.0121   1.0000
  10.000   1.3244   0.02718   0.02064  -0.0457   0.0119   1.0000
  10.250   1.3278   0.02877   0.02233  -0.0432   0.0117   1.0000
  10.500   1.3301   0.03059   0.02425  -0.0411   0.0115   1.0000
  10.750   1.3323   0.03262   0.02636  -0.0392   0.0113   1.0000
  11.000   1.3352   0.03474   0.02857  -0.0378   0.0112   1.0000
  11.250   1.3389   0.03690   0.03082  -0.0366   0.0109   1.0000
  11.500   1.3432   0.03908   0.03308  -0.0357   0.0106   1.0000
  11.750   1.3474   0.04134   0.03539  -0.0350   0.0103   1.0000
  12.000   1.3511   0.04371   0.03783  -0.0344   0.0100   1.0000
  12.250   1.3553   0.04610   0.04029  -0.0335   0.0098   1.0000
  12.500   1.3605   0.04844   0.04271  -0.0324   0.0097   1.0000
  12.750   1.3665   0.05080   0.04514  -0.0312   0.0097   1.0000
  13.000   1.3727   0.05321   0.04766  -0.0301   0.0097   1.0000
  13.250   1.3732   0.05673   0.05149  -0.0288   0.0103   1.0000
  13.500   1.1908   0.05920   0.05442  -0.0214   0.0102   1.0000
  13.750   1.1884   0.06306   0.05840  -0.0206   0.0103   1.0000
  14.000   1.1827   0.06733   0.06285  -0.0199   0.0105   1.0000
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