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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 100,000
Max Cl/Cd: 53.78 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa22-il-100000.txt
Download as CSV file: xf-usa22-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3690   0.10763   0.10292  -0.0115   1.0000   0.0757
  -8.500  -0.3739   0.10603   0.10141  -0.0161   1.0000   0.0778
  -8.250  -0.3822   0.10466   0.10015  -0.0215   1.0000   0.0784
  -8.000  -0.3678   0.09848   0.09399  -0.0190   1.0000   0.0800
  -7.750  -0.3520   0.09456   0.09007  -0.0169   1.0000   0.0831
  -7.500  -0.3469   0.09166   0.08722  -0.0176   1.0000   0.0864
  -7.250  -0.3474   0.08909   0.08471  -0.0202   1.0000   0.0899
  -7.000  -0.3490   0.08693   0.08262  -0.0354   1.0000   0.0925
  -6.750  -0.3403   0.08202   0.07779  -0.0273   1.0000   0.0945
  -6.500  -0.3308   0.07916   0.07497  -0.0251   1.0000   0.0981
  -6.250  -0.3255   0.07633   0.07219  -0.0290   1.0000   0.1041
  -6.000  -0.2909   0.06328   0.05970  -0.0213   1.0000   0.1118
  -5.750  -0.2996   0.06148   0.05798  -0.0203   1.0000   0.1157
  -5.500  -0.3076   0.06704   0.06293  -0.0367   1.0000   0.1209
  -5.250  -0.3056   0.06481   0.06085  -0.0305   1.0000   0.1248
  -5.000  -0.2963   0.06200   0.05792  -0.0355   1.0000   0.1353
  -4.750  -0.2953   0.05977   0.05582  -0.0312   1.0000   0.1382
  -4.500  -0.2841   0.05733   0.05324  -0.0348   1.0000   0.1499
  -4.250  -0.2713   0.05463   0.05064  -0.0331   0.9975   0.1546
  -4.000  -0.2156   0.04995   0.04565  -0.0439   0.9878   0.1795
  -3.750  -0.1407   0.03319   0.02733  -0.0599   0.9835   0.0947
  -3.500  -0.0909   0.02770   0.02102  -0.0647   0.9747   0.0867
  -3.250  -0.0394   0.02453   0.01690  -0.0690   0.9651   0.0920
  -3.000   0.0118   0.02204   0.01416  -0.0736   0.9565   0.0997
  -2.750   0.0604   0.02023   0.01197  -0.0771   0.9445   0.1089
  -2.500   0.1070   0.01899   0.01062  -0.0802   0.9313   0.1226
  -2.250   0.1505   0.01784   0.00941  -0.0825   0.9167   0.1363
  -2.000   0.1901   0.01690   0.00854  -0.0840   0.9002   0.1601
  -1.750   0.2234   0.01599   0.00788  -0.0841   0.8806   0.2080
  -1.500   0.2527   0.01579   0.00789  -0.0835   0.8582   0.3161
  -1.250   0.2800   0.01549   0.00749  -0.0825   0.8355   0.3653
  -1.000   0.3057   0.01503   0.00705  -0.0813   0.8129   0.4085
  -0.750   0.3306   0.01447   0.00664  -0.0800   0.7899   0.4588
  -0.500   0.3676   0.01275   0.00628  -0.0804   0.7686   1.0000
  -0.250   0.3944   0.01296   0.00609  -0.0796   0.7463   1.0000
   0.000   0.4208   0.01318   0.00597  -0.0787   0.7262   1.0000
   0.250   0.4471   0.01344   0.00592  -0.0779   0.7079   1.0000
   0.500   0.4730   0.01373   0.00596  -0.0773   0.6893   1.0000
   0.750   0.4990   0.01402   0.00603  -0.0766   0.6725   1.0000
   1.000   0.5251   0.01431   0.00612  -0.0760   0.6570   1.0000
   1.250   0.5512   0.01460   0.00624  -0.0754   0.6423   1.0000
   1.500   0.5772   0.01489   0.00637  -0.0749   0.6283   1.0000
   1.750   0.6033   0.01518   0.00652  -0.0743   0.6148   1.0000
   2.000   0.6294   0.01546   0.00667  -0.0738   0.6019   1.0000
   2.250   0.6556   0.01575   0.00683  -0.0732   0.5895   1.0000
   2.500   0.6817   0.01603   0.00700  -0.0727   0.5773   1.0000
   2.750   0.7075   0.01633   0.00724  -0.0722   0.5646   1.0000
   3.000   0.7334   0.01666   0.00752  -0.0717   0.5524   1.0000
   3.250   0.7593   0.01699   0.00781  -0.0713   0.5408   1.0000
   3.500   0.7854   0.01732   0.00807  -0.0708   0.5296   1.0000
   3.750   0.8116   0.01765   0.00832  -0.0703   0.5188   1.0000
   4.000   0.8370   0.01802   0.00871  -0.0698   0.5067   1.0000
   4.250   0.8625   0.01842   0.00914  -0.0693   0.4950   1.0000
   4.500   0.8882   0.01883   0.00954  -0.0689   0.4837   1.0000
   4.750   0.9140   0.01923   0.00990  -0.0684   0.4725   1.0000
   5.000   0.9396   0.01963   0.01030  -0.0679   0.4609   1.0000
   5.250   0.9644   0.02009   0.01082  -0.0673   0.4483   1.0000
   5.500   0.9892   0.02060   0.01140  -0.0668   0.4361   1.0000
   5.750   1.0141   0.02114   0.01199  -0.0663   0.4244   1.0000
   6.000   1.0393   0.02167   0.01257  -0.0657   0.4133   1.0000
   6.250   1.0648   0.02217   0.01306  -0.0652   0.4023   1.0000
   6.500   1.0885   0.02275   0.01378  -0.0646   0.3901   1.0000
   6.750   1.1121   0.02305   0.01415  -0.0638   0.3763   1.0000
   7.000   1.1354   0.02301   0.01413  -0.0628   0.3604   1.0000
   7.250   1.1582   0.02304   0.01419  -0.0618   0.3452   1.0000
   7.500   1.1805   0.02307   0.01428  -0.0608   0.3301   1.0000
   7.750   1.2016   0.02313   0.01447  -0.0597   0.3143   1.0000
   8.000   1.2213   0.02310   0.01462  -0.0584   0.2945   1.0000
   8.250   1.2415   0.02322   0.01490  -0.0571   0.2763   1.0000
   8.500   1.2589   0.02341   0.01513  -0.0556   0.2474   1.0000
   8.750   1.2762   0.02401   0.01573  -0.0542   0.2151   1.0000
   9.000   1.2907   0.02510   0.01669  -0.0526   0.1672   1.0000
   9.250   1.2891   0.02795   0.01874  -0.0499   0.0716   1.0000
   9.500   1.2916   0.03036   0.02101  -0.0473   0.0542   1.0000
   9.750   1.2968   0.03230   0.02306  -0.0450   0.0485   1.0000
  10.000   1.2967   0.03439   0.02531  -0.0423   0.0452   1.0000
  10.500   1.2884   0.03924   0.03051  -0.0378   0.0424   1.0000
  10.750   1.2839   0.04205   0.03352  -0.0366   0.0417   1.0000
  11.000   1.2783   0.04526   0.03692  -0.0360   0.0412   1.0000
  11.250   1.2726   0.04878   0.04061  -0.0360   0.0407   1.0000
  11.500   1.2676   0.05237   0.04434  -0.0361   0.0403   1.0000
  11.750   1.2644   0.05576   0.04785  -0.0360   0.0398   1.0000
  12.000   1.2644   0.05868   0.05086  -0.0353   0.0394   1.0000
  12.250   1.2691   0.06091   0.05315  -0.0339   0.0390   1.0000
  12.500   1.2779   0.06270   0.05498  -0.0320   0.0382   1.0000
  12.750   1.2880   0.06453   0.05683  -0.0301   0.0370   1.0000
  13.000   1.3030   0.06608   0.05841  -0.0277   0.0357   1.0000
  13.250   1.3222   0.06787   0.06029  -0.0251   0.0353   1.0000
  13.500   1.3320   0.07070   0.06334  -0.0239   0.0355   1.0000
  13.750   1.3344   0.07425   0.06717  -0.0235   0.0359   1.0000
  14.000   1.3309   0.07840   0.07163  -0.0237   0.0363   1.0000
  14.250   1.3235   0.08309   0.07661  -0.0245   0.0369   1.0000
  14.500   1.3081   0.08865   0.08248  -0.0264   0.0374   1.0000
  14.750   1.2898   0.09480   0.08891  -0.0290   0.0378   1.0000
  15.000   1.2698   0.10145   0.09583  -0.0324   0.0383   1.0000
  15.250   1.2484   0.10871   0.10333  -0.0364   0.0387   1.0000
  15.500   1.2259   0.11668   0.11152  -0.0413   0.0391   1.0000
  15.750   1.2021   0.12550   0.12054  -0.0470   0.0395   1.0000
  16.000   1.1767   0.13533   0.13057  -0.0537   0.0399   1.0000
  16.250   1.1490   0.14669   0.14207  -0.0616   0.0404   1.0000
  16.500   1.1197   0.15971   0.15517  -0.0705   0.0412   1.0000
  16.750   1.0985   0.17157   0.16705  -0.0778   0.0423   1.0000
  17.000   1.0864   0.18199   0.17749  -0.0836   0.0439   1.0000
  17.250   0.7919   0.17347   0.16915  -0.0599   0.0521   1.0000
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