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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 200,000
Max Cl/Cd: 73.53 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa22-il-200000-n5.txt
Download as CSV file: xf-usa22-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2634   0.09215   0.08901  -0.0235   1.0000   0.0152
  -9.000  -0.3647   0.10266   0.09930  -0.0146   1.0000   0.0153
  -8.750  -0.3594   0.09925   0.09592  -0.0156   1.0000   0.0149
  -8.500  -0.3549   0.09577   0.09247  -0.0170   1.0000   0.0146
  -8.250  -0.3511   0.09224   0.08898  -0.0185   1.0000   0.0144
  -8.000  -0.3481   0.08869   0.08547  -0.0202   1.0000   0.0142
  -7.750  -0.3464   0.08518   0.08201  -0.0218   1.0000   0.0140
  -7.500  -0.3466   0.08175   0.07865  -0.0232   1.0000   0.0138
  -7.250  -0.3447   0.07795   0.07490  -0.0257   1.0000   0.0137
  -7.000  -0.3426   0.07399   0.07101  -0.0285   1.0000   0.0136
  -6.750  -0.3408   0.07002   0.06709  -0.0310   1.0000   0.0137
  -6.500  -0.3143   0.06295   0.05994  -0.0413   0.9893   0.0143
  -6.000  -0.2491   0.04321   0.03984  -0.0654   0.9622   0.0150
  -5.750  -0.2175   0.02580   0.02109  -0.0773   0.9488   0.0152
  -5.500  -0.1856   0.02136   0.01579  -0.0796   0.9379   0.0159
  -5.250  -0.1546   0.01907   0.01305  -0.0809   0.9254   0.0175
  -5.000  -0.1225   0.01842   0.01223  -0.0819   0.9117   0.0198
  -4.750  -0.0919   0.01690   0.01031  -0.0823   0.8967   0.0222
  -4.500  -0.0626   0.01564   0.00873  -0.0823   0.8804   0.0247
  -4.250  -0.0344   0.01535   0.00836  -0.0822   0.8613   0.0287
  -4.000  -0.0066   0.01474   0.00747  -0.0818   0.8406   0.0332
  -3.750   0.0202   0.01432   0.00696  -0.0814   0.8175   0.0383
  -3.500   0.0473   0.01404   0.00644  -0.0808   0.7937   0.0434
  -3.250   0.0734   0.01352   0.00579  -0.0803   0.7704   0.0489
  -3.000   0.0999   0.01327   0.00535  -0.0798   0.7481   0.0544
  -2.750   0.1265   0.01306   0.00491  -0.0792   0.7267   0.0579
  -2.500   0.1526   0.01262   0.00435  -0.0787   0.7073   0.0618
  -2.250   0.1793   0.01240   0.00397  -0.0783   0.6890   0.0660
  -2.000   0.2061   0.01225   0.00367  -0.0779   0.6706   0.0710
  -1.750   0.2329   0.01205   0.00339  -0.0775   0.6524   0.0802
  -1.500   0.2596   0.01186   0.00317  -0.0772   0.6348   0.0965
  -1.250   0.2861   0.01163   0.00303  -0.0769   0.6177   0.1532
  -1.000   0.3127   0.01152   0.00298  -0.0766   0.6005   0.2024
  -0.750   0.3395   0.01152   0.00297  -0.0763   0.5836   0.2448
  -0.500   0.3664   0.01157   0.00297  -0.0760   0.5676   0.2761
  -0.250   0.3933   0.01162   0.00295  -0.0757   0.5523   0.2978
   0.000   0.4202   0.01168   0.00292  -0.0754   0.5379   0.3171
   0.250   0.4469   0.01169   0.00292  -0.0752   0.5246   0.3381
   0.500   0.4736   0.01172   0.00291  -0.0749   0.5121   0.3608
   0.750   0.5002   0.01172   0.00289  -0.0746   0.5002   0.3802
   1.250   0.5486   0.01097   0.00295  -0.0732   0.4778   0.6956
   1.750   0.6120   0.01082   0.00302  -0.0743   0.4553   1.0000
   2.000   0.6389   0.01099   0.00309  -0.0741   0.4452   1.0000
   2.250   0.6656   0.01117   0.00319  -0.0738   0.4365   1.0000
   2.500   0.6923   0.01136   0.00330  -0.0736   0.4283   1.0000
   2.750   0.7191   0.01153   0.00343  -0.0733   0.4208   1.0000
   3.000   0.7457   0.01173   0.00357  -0.0731   0.4132   1.0000
   3.250   0.7724   0.01191   0.00373  -0.0729   0.4055   1.0000
   3.500   0.7988   0.01212   0.00389  -0.0726   0.3978   1.0000
   3.750   0.8255   0.01230   0.00408  -0.0724   0.3901   1.0000
   4.000   0.8519   0.01252   0.00427  -0.0721   0.3828   1.0000
   4.250   0.8785   0.01270   0.00448  -0.0719   0.3751   1.0000
   4.500   0.9046   0.01293   0.00471  -0.0716   0.3675   1.0000
   4.750   0.9311   0.01312   0.00495  -0.0714   0.3591   1.0000
   5.000   0.9571   0.01336   0.00519  -0.0711   0.3506   1.0000
   5.250   0.9831   0.01358   0.00547  -0.0708   0.3408   1.0000
   5.500   1.0090   0.01382   0.00575  -0.0705   0.3310   1.0000
   5.750   1.0343   0.01408   0.00602  -0.0701   0.3174   1.0000
   6.000   1.0588   0.01440   0.00628  -0.0696   0.2968   1.0000
   6.250   1.0831   0.01476   0.00663  -0.0692   0.2776   1.0000
   6.500   1.1064   0.01521   0.00700  -0.0686   0.2537   1.0000
   6.750   1.1283   0.01584   0.00747  -0.0679   0.2226   1.0000
   7.000   1.1496   0.01655   0.00803  -0.0672   0.1905   1.0000
   7.250   1.1692   0.01748   0.00873  -0.0663   0.1491   1.0000
   7.500   1.1720   0.02041   0.01081  -0.0637   0.0241   1.0000
   7.750   1.1915   0.02133   0.01184  -0.0625   0.0185   1.0000
   8.000   1.2116   0.02211   0.01279  -0.0615   0.0168   1.0000
   8.250   1.2307   0.02296   0.01381  -0.0604   0.0150   1.0000
   8.500   1.2481   0.02395   0.01498  -0.0591   0.0136   1.0000
   8.750   1.2632   0.02510   0.01632  -0.0575   0.0128   1.0000
   9.000   1.2748   0.02646   0.01788  -0.0557   0.0121   1.0000
   9.250   1.2810   0.02813   0.01975  -0.0534   0.0115   1.0000
   9.500   1.2775   0.03017   0.02198  -0.0500   0.0110   1.0000
   9.750   1.2750   0.03224   0.02421  -0.0474   0.0106   1.0000
  10.000   1.2805   0.03386   0.02596  -0.0458   0.0101   1.0000
  10.250   1.2822   0.03596   0.02819  -0.0445   0.0097   1.0000
  10.500   1.2809   0.03855   0.03090  -0.0435   0.0095   1.0000
  10.750   1.2793   0.04142   0.03390  -0.0430   0.0093   1.0000
  11.000   1.2776   0.04449   0.03708  -0.0427   0.0091   1.0000
  11.250   1.2761   0.04763   0.04033  -0.0426   0.0089   1.0000
  11.500   1.2750   0.05079   0.04358  -0.0425   0.0087   1.0000
  11.750   1.2744   0.05390   0.04679  -0.0423   0.0086   1.0000
  12.000   1.2743   0.05693   0.04991  -0.0421   0.0084   1.0000
  12.250   1.2751   0.05987   0.05293  -0.0417   0.0083   1.0000
  12.500   1.2766   0.06270   0.05584  -0.0413   0.0081   1.0000
  12.750   1.2784   0.06553   0.05875  -0.0408   0.0080   1.0000
  13.000   1.2797   0.06849   0.06179  -0.0406   0.0078   1.0000
  13.250   1.2804   0.07151   0.06489  -0.0405   0.0076   1.0000
  13.500   1.2814   0.07443   0.06785  -0.0400   0.0073   1.0000
  13.750   1.2833   0.07739   0.07088  -0.0390   0.0070   1.0000
  14.000   1.2781   0.08160   0.07535  -0.0405   0.0069   1.0000
  14.250   1.2737   0.08582   0.07977  -0.0417   0.0067   1.0000
  14.500   1.2697   0.09004   0.08418  -0.0428   0.0066   1.0000
  14.750   1.2651   0.09447   0.08878  -0.0440   0.0065   1.0000
  15.000   1.2592   0.09918   0.09367  -0.0455   0.0065   1.0000
  15.250   1.2522   0.10422   0.09889  -0.0474   0.0064   1.0000
  15.500   1.2446   0.10948   0.10433  -0.0495   0.0064   1.0000
  15.750   1.2361   0.11509   0.11012  -0.0521   0.0064   1.0000
  16.000   1.2271   0.12095   0.11616  -0.0549   0.0064   1.0000
  16.250   1.2175   0.12709   0.12247  -0.0581   0.0064   1.0000
  16.500   1.2079   0.13344   0.12898  -0.0616   0.0064   1.0000
  16.750   1.1980   0.14013   0.13584  -0.0655   0.0064   1.0000
  17.000   1.1881   0.14707   0.14293  -0.0697   0.0064   1.0000
  17.250   1.1781   0.15429   0.15030  -0.0742   0.0064   1.0000
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