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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 100,000
Max Cl/Cd: 55.71 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa22-il-100000-n5.txt
Download as CSV file: xf-usa22-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3364   0.09076   0.08625  -0.0217   1.0000   0.0306
  -7.500  -0.3347   0.08744   0.08300  -0.0227   1.0000   0.0294
  -7.250  -0.3338   0.08398   0.07962  -0.0244   1.0000   0.0284
  -7.000  -0.3314   0.08010   0.07581  -0.0270   1.0000   0.0275
  -6.750  -0.3292   0.07589   0.07167  -0.0300   1.0000   0.0266
  -6.500  -0.3272   0.07082   0.06667  -0.0340   1.0000   0.0256
  -6.000  -0.3156   0.05961   0.05545  -0.0418   1.0000   0.0245
  -5.750  -0.2960   0.05811   0.05393  -0.0434   0.9954   0.0262
  -5.500  -0.2586   0.05255   0.04821  -0.0516   0.9854   0.0281
  -5.250  -0.2181   0.04373   0.03903  -0.0616   0.9747   0.0285
  -5.000  -0.1776   0.03450   0.02907  -0.0699   0.9649   0.0291
  -4.750  -0.1405   0.02855   0.02216  -0.0743   0.9540   0.0315
  -4.500  -0.1055   0.02543   0.01839  -0.0766   0.9422   0.0351
  -4.250  -0.0705   0.02343   0.01601  -0.0783   0.9301   0.0385
  -4.000  -0.0348   0.02168   0.01367  -0.0796   0.9173   0.0450
  -3.750  -0.0015   0.02020   0.01203  -0.0807   0.9032   0.0508
  -3.500   0.0315   0.01917   0.01062  -0.0814   0.8876   0.0591
  -3.250   0.0622   0.01817   0.00955  -0.0818   0.8705   0.0669
  -3.000   0.0926   0.01739   0.00849  -0.0818   0.8524   0.0731
  -2.750   0.1204   0.01661   0.00765  -0.0815   0.8319   0.0784
  -2.500   0.1486   0.01610   0.00696  -0.0811   0.8112   0.0856
  -2.250   0.1762   0.01562   0.00642  -0.0807   0.7899   0.0968
  -2.000   0.2038   0.01521   0.00593  -0.0802   0.7689   0.1095
  -1.750   0.2312   0.01482   0.00554  -0.0797   0.7488   0.1393
  -1.500   0.2581   0.01453   0.00539  -0.0792   0.7285   0.2026
  -1.250   0.2853   0.01454   0.00532  -0.0788   0.7090   0.2587
  -1.000   0.3122   0.01457   0.00521  -0.0782   0.6905   0.2916
  -0.750   0.3389   0.01458   0.00512  -0.0778   0.6719   0.3246
  -0.500   0.3655   0.01454   0.00501  -0.0773   0.6540   0.3589
  -0.250   0.3921   0.01443   0.00486  -0.0769   0.6370   0.3907
   0.000   0.4185   0.01428   0.00471  -0.0765   0.6209   0.4230
   0.250   0.4424   0.01372   0.00465  -0.0757   0.6058   0.5524
   0.750   0.5053   0.01327   0.00451  -0.0762   0.5761   1.0000
   1.000   0.5319   0.01347   0.00452  -0.0758   0.5628   1.0000
   1.250   0.5584   0.01368   0.00456  -0.0754   0.5501   1.0000
   1.500   0.5849   0.01390   0.00462  -0.0750   0.5380   1.0000
   1.750   0.6112   0.01413   0.00469  -0.0746   0.5265   1.0000
   2.000   0.6375   0.01436   0.00478  -0.0742   0.5150   1.0000
   2.250   0.6637   0.01460   0.00492  -0.0739   0.5031   1.0000
   2.500   0.6899   0.01484   0.00507  -0.0735   0.4920   1.0000
   2.750   0.7160   0.01509   0.00523  -0.0731   0.4815   1.0000
   3.000   0.7420   0.01536   0.00542  -0.0727   0.4713   1.0000
   3.250   0.7681   0.01562   0.00564  -0.0724   0.4608   1.0000
   3.500   0.7941   0.01589   0.00587  -0.0720   0.4513   1.0000
   3.750   0.8200   0.01618   0.00613  -0.0717   0.4421   1.0000
   4.000   0.8459   0.01647   0.00643  -0.0713   0.4325   1.0000
   4.250   0.8716   0.01678   0.00671  -0.0709   0.4240   1.0000
   4.500   0.8973   0.01708   0.00707  -0.0706   0.4146   1.0000
   4.750   0.9229   0.01739   0.00742  -0.0702   0.4053   1.0000
   5.000   0.9482   0.01773   0.00774  -0.0698   0.3965   1.0000
   5.250   0.9735   0.01804   0.00818  -0.0694   0.3863   1.0000
   5.500   0.9987   0.01839   0.00859  -0.0690   0.3772   1.0000
   5.750   1.0236   0.01875   0.00900  -0.0685   0.3682   1.0000
   6.000   1.0485   0.01911   0.00950  -0.0681   0.3581   1.0000
   6.250   1.0731   0.01949   0.00999  -0.0675   0.3486   1.0000
   6.500   1.0972   0.01987   0.01044  -0.0670   0.3382   1.0000
   6.750   1.1199   0.02016   0.01083  -0.0662   0.3196   1.0000
   7.000   1.1421   0.02050   0.01121  -0.0654   0.2992   1.0000
   7.250   1.1626   0.02092   0.01159  -0.0645   0.2714   1.0000
   7.500   1.1831   0.02150   0.01219  -0.0636   0.2467   1.0000
   7.750   1.2024   0.02225   0.01287  -0.0625   0.2186   1.0000
   8.000   1.2188   0.02331   0.01375  -0.0613   0.1802   1.0000
   8.250   1.2323   0.02476   0.01491  -0.0598   0.1178   1.0000
   8.500   1.2260   0.02829   0.01762  -0.0566   0.0303   1.0000
   8.750   1.2372   0.02985   0.01931  -0.0548   0.0257   1.0000
   9.000   1.2489   0.03126   0.02095  -0.0530   0.0239   1.0000
   9.250   1.2577   0.03283   0.02276  -0.0510   0.0224   1.0000
   9.500   1.2614   0.03459   0.02474  -0.0486   0.0211   1.0000
   9.750   1.2604   0.03671   0.02707  -0.0462   0.0199   1.0000
  10.000   1.2550   0.03933   0.02997  -0.0442   0.0189   1.0000
  10.250   1.2469   0.04249   0.03337  -0.0430   0.0183   1.0000
  10.500   1.2372   0.04620   0.03731  -0.0427   0.0179   1.0000
  10.750   1.2303   0.05001   0.04128  -0.0430   0.0178   1.0000
  11.000   1.2230   0.05415   0.04562  -0.0439   0.0176   1.0000
  11.250   1.2152   0.05857   0.05022  -0.0450   0.0175   1.0000
  11.500   1.2071   0.06313   0.05494  -0.0462   0.0174   1.0000
  11.750   1.1996   0.06764   0.05960  -0.0473   0.0172   1.0000
  12.000   1.1933   0.07193   0.06402  -0.0482   0.0171   1.0000
  12.250   1.1889   0.07582   0.06803  -0.0488   0.0169   1.0000
  12.500   1.1873   0.07917   0.07147  -0.0489   0.0167   1.0000
  12.750   1.1881   0.08204   0.07443  -0.0486   0.0164   1.0000
  13.000   1.1912   0.08460   0.07709  -0.0481   0.0159   1.0000
  13.250   1.1945   0.08723   0.07980  -0.0476   0.0153   1.0000
  13.500   1.1987   0.08972   0.08240  -0.0471   0.0147   1.0000
  13.750   1.2034   0.09220   0.08496  -0.0465   0.0142   1.0000
  14.000   1.2092   0.09460   0.08748  -0.0457   0.0139   1.0000
  14.250   1.2131   0.09747   0.09049  -0.0453   0.0137   1.0000
  14.500   1.2143   0.10093   0.09411  -0.0455   0.0136   1.0000
  14.750   1.2136   0.10485   0.09820  -0.0462   0.0135   1.0000
  15.000   1.2105   0.10931   0.10284  -0.0475   0.0135   1.0000
  15.250   1.2057   0.11421   0.10794  -0.0493   0.0134   1.0000
  15.500   1.1993   0.11955   0.11353  -0.0516   0.0134   1.0000
  15.750   1.1914   0.12534   0.11952  -0.0545   0.0135   1.0000
  16.000   1.1824   0.13160   0.12597  -0.0579   0.0135   1.0000
  16.250   1.1724   0.13834   0.13290  -0.0618   0.0136   1.0000
  16.500   1.1616   0.14559   0.14033  -0.0662   0.0137   1.0000
  16.750   1.1500   0.15338   0.14830  -0.0712   0.0138   1.0000
  17.000   1.1378   0.16178   0.15686  -0.0766   0.0139   1.0000
  17.250   1.1250   0.17091   0.16608  -0.0826   0.0141   1.0000
  17.500   1.1117   0.18090   0.17620  -0.0891   0.0143   1.0000
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