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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.55 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa22-il-1000000-n5.txt
Download as CSV file: xf-usa22-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4234   0.12509   0.12348  -0.0006   1.0000   0.0033
 -10.750  -0.4196   0.12098   0.11939  -0.0021   1.0000   0.0033
  -9.250  -0.5851   0.02359   0.02092  -0.0765   0.9866   0.0036
  -9.000  -0.5559   0.02079   0.01781  -0.0791   0.9763   0.0037
  -8.750  -0.5260   0.01887   0.01564  -0.0809   0.9619   0.0038
  -8.500  -0.4972   0.01738   0.01391  -0.0820   0.9445   0.0040
  -8.250  -0.4709   0.01628   0.01258  -0.0821   0.9265   0.0041
  -8.000  -0.4457   0.01538   0.01146  -0.0819   0.9103   0.0043
  -7.750  -0.4204   0.01461   0.01049  -0.0816   0.8954   0.0045
  -7.500  -0.3948   0.01394   0.00964  -0.0813   0.8797   0.0047
  -7.250  -0.3689   0.01333   0.00885  -0.0809   0.8629   0.0048
  -7.000  -0.3435   0.01242   0.00769  -0.0806   0.8444   0.0050
  -6.750  -0.3177   0.01183   0.00690  -0.0802   0.8219   0.0053
  -6.500  -0.2917   0.01144   0.00633  -0.0798   0.7916   0.0056
  -6.250  -0.2656   0.01112   0.00581  -0.0794   0.7599   0.0059
  -6.000  -0.2391   0.01082   0.00533  -0.0791   0.7344   0.0063
  -5.750  -0.2121   0.01051   0.00488  -0.0788   0.7154   0.0067
  -5.500  -0.1848   0.01025   0.00448  -0.0786   0.6986   0.0070
  -5.250  -0.1575   0.00994   0.00403  -0.0784   0.6822   0.0075
  -5.000  -0.1302   0.00965   0.00363  -0.0782   0.6657   0.0086
  -4.750  -0.1027   0.00944   0.00333  -0.0780   0.6501   0.0096
  -4.500  -0.0750   0.00927   0.00305  -0.0779   0.6355   0.0104
  -4.250  -0.0473   0.00906   0.00274  -0.0777   0.6199   0.0123
  -4.000  -0.0198   0.00890   0.00252  -0.0775   0.6031   0.0149
  -3.750   0.0079   0.00877   0.00234  -0.0774   0.5857   0.0207
  -3.500   0.0356   0.00869   0.00219  -0.0773   0.5690   0.0247
  -3.250   0.0634   0.00863   0.00208  -0.0772   0.5517   0.0292
  -3.000   0.0912   0.00861   0.00198  -0.0770   0.5337   0.0323
  -2.750   0.1190   0.00862   0.00190  -0.0769   0.5165   0.0336
  -2.500   0.1467   0.00854   0.00176  -0.0768   0.5011   0.0374
  -2.250   0.1745   0.00852   0.00168  -0.0767   0.4864   0.0405
  -2.000   0.2024   0.00851   0.00160  -0.0766   0.4735   0.0427
  -1.750   0.2304   0.00849   0.00151  -0.0765   0.4625   0.0438
  -1.500   0.2583   0.00846   0.00142  -0.0764   0.4522   0.0460
  -1.250   0.2862   0.00842   0.00133  -0.0763   0.4426   0.0505
  -1.000   0.3142   0.00840   0.00128  -0.0762   0.4341   0.0547
  -0.750   0.3421   0.00841   0.00123  -0.0762   0.4250   0.0586
  -0.500   0.3699   0.00837   0.00119  -0.0761   0.4144   0.0722
  -0.250   0.3973   0.00820   0.00117  -0.0761   0.4044   0.1391
   0.000   0.4250   0.00820   0.00117  -0.0760   0.3958   0.1598
   0.250   0.4530   0.00815   0.00117  -0.0760   0.3900   0.1841
   0.500   0.4807   0.00812   0.00121  -0.0759   0.3832   0.2231
   0.750   0.5088   0.00813   0.00124  -0.0759   0.3775   0.2442
   1.000   0.5367   0.00814   0.00128  -0.0759   0.3718   0.2631
   1.250   0.5646   0.00819   0.00133  -0.0758   0.3665   0.2774
   1.750   0.6206   0.00826   0.00142  -0.0758   0.3555   0.3027
   2.000   0.6484   0.00831   0.00148  -0.0758   0.3500   0.3123
   2.250   0.6763   0.00837   0.00154  -0.0757   0.3430   0.3190
   2.500   0.7040   0.00844   0.00160  -0.0757   0.3357   0.3278
   2.750   0.7317   0.00851   0.00168  -0.0757   0.3275   0.3389
   3.000   0.7593   0.00856   0.00176  -0.0756   0.3204   0.3584
   3.250   0.7868   0.00861   0.00185  -0.0756   0.3121   0.3869
   3.500   0.8090   0.00771   0.00204  -0.0748   0.3047   0.8347
   4.000   0.8682   0.00773   0.00226  -0.0755   0.2851   1.0000
   4.250   0.8948   0.00795   0.00241  -0.0753   0.2696   1.0000
   4.500   0.9208   0.00825   0.00260  -0.0751   0.2473   1.0000
   4.750   0.9471   0.00851   0.00278  -0.0749   0.2315   1.0000
   5.000   0.9728   0.00885   0.00300  -0.0746   0.2115   1.0000
   5.250   0.9983   0.00920   0.00325  -0.0743   0.1914   1.0000
   5.500   1.0238   0.00955   0.00351  -0.0740   0.1727   1.0000
   5.750   1.0489   0.00996   0.00380  -0.0737   0.1522   1.0000
   6.000   1.0682   0.01114   0.00454  -0.0727   0.0788   1.0000
   6.250   1.0880   0.01228   0.00541  -0.0717   0.0158   1.0000
   6.500   1.1132   0.01262   0.00576  -0.0713   0.0113   1.0000
   6.750   1.1387   0.01292   0.00609  -0.0710   0.0100   1.0000
   7.000   1.1638   0.01325   0.00645  -0.0707   0.0088   1.0000
   7.250   1.1882   0.01367   0.00690  -0.0702   0.0075   1.0000
   7.500   1.2127   0.01407   0.00733  -0.0698   0.0067   1.0000
   7.750   1.2371   0.01444   0.00773  -0.0694   0.0060   1.0000
   8.000   1.2610   0.01486   0.00817  -0.0689   0.0055   1.0000
   8.250   1.2840   0.01538   0.00872  -0.0683   0.0049   1.0000
   8.500   1.3066   0.01592   0.00932  -0.0677   0.0046   1.0000
   8.750   1.3293   0.01643   0.00988  -0.0671   0.0043   1.0000
   9.000   1.3515   0.01696   0.01048  -0.0664   0.0040   1.0000
   9.250   1.3733   0.01749   0.01105  -0.0657   0.0037   1.0000
   9.500   1.3948   0.01803   0.01162  -0.0650   0.0035   1.0000
   9.750   1.4147   0.01870   0.01234  -0.0641   0.0032   1.0000
  10.000   1.4320   0.01959   0.01332  -0.0628   0.0030   1.0000
  10.250   1.4504   0.02032   0.01411  -0.0617   0.0029   1.0000
  10.500   1.4672   0.02112   0.01500  -0.0604   0.0028   1.0000
  10.750   1.4824   0.02200   0.01596  -0.0589   0.0027   1.0000
  11.000   1.4957   0.02292   0.01697  -0.0572   0.0026   1.0000
  11.250   1.5046   0.02392   0.01807  -0.0549   0.0025   1.0000
  11.500   1.5117   0.02503   0.01928  -0.0525   0.0024   1.0000
  11.750   1.5180   0.02627   0.02060  -0.0504   0.0023   1.0000
  12.000   1.5229   0.02774   0.02216  -0.0486   0.0023   1.0000
  12.250   1.5270   0.02942   0.02393  -0.0471   0.0022   1.0000
  12.500   1.5294   0.03143   0.02605  -0.0459   0.0022   1.0000
  12.750   1.5315   0.03369   0.02840  -0.0452   0.0021   1.0000
  13.000   1.5322   0.03635   0.03116  -0.0450   0.0021   1.0000
  13.250   1.5296   0.03962   0.03455  -0.0453   0.0020   1.0000
  13.500   1.5263   0.04321   0.03825  -0.0459   0.0020   1.0000
  13.750   1.5190   0.04745   0.04261  -0.0468   0.0020   1.0000
  14.000   1.5094   0.05215   0.04744  -0.0480   0.0019   1.0000
  14.250   1.4962   0.05743   0.05285  -0.0494   0.0019   1.0000
  14.500   1.4829   0.06277   0.05832  -0.0508   0.0019   1.0000
  14.750   1.4677   0.06841   0.06408  -0.0523   0.0019   1.0000
  15.000   1.4515   0.07426   0.07005  -0.0540   0.0018   1.0000
  15.250   1.4338   0.08044   0.07635  -0.0557   0.0018   1.0000
  15.500   1.4212   0.08594   0.08195  -0.0573   0.0018   1.0000
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