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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 50,000
Max Cl/Cd: 32.51 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa22-il-50000.txt
Download as CSV file: xf-usa22-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3735   0.10521   0.09902  -0.0134   1.0000   0.1922
  -7.500  -0.3467   0.09862   0.09238  -0.0109   1.0000   0.2014
  -7.250  -0.3642   0.09901   0.09296  -0.0154   1.0000   0.2066
  -7.000  -0.3415   0.09304   0.08698  -0.0116   1.0000   0.2159
  -6.500  -0.3378   0.08793   0.08207  -0.0141   1.0000   0.2336
  -5.750  -0.3299   0.07998   0.07441  -0.0167   1.0000   0.2657
  -5.500  -0.3260   0.07749   0.07198  -0.0165   1.0000   0.2792
  -5.250  -0.3168   0.07344   0.06803  -0.0128   1.0000   0.2886
  -5.000  -0.3146   0.07075   0.06543  -0.0124   1.0000   0.2997
  -4.750  -0.3129   0.06824   0.06298  -0.0121   1.0000   0.3124
  -4.500  -0.3110   0.06575   0.06057  -0.0113   1.0000   0.3263
  -4.250  -0.3088   0.06326   0.05815  -0.0098   1.0000   0.3415
  -4.000  -0.3076   0.06137   0.05630  -0.0099   1.0000   0.3664
  -3.750  -0.3071   0.05858   0.05363  -0.0056   1.0000   0.3856
  -3.500  -0.3072   0.05632   0.05145  -0.0029   1.0000   0.4141
  -3.250  -0.1738   0.04181   0.03473  -0.0462   1.0000   0.1630
  -3.000  -0.1513   0.03889   0.03157  -0.0474   1.0000   0.1617
  -2.750  -0.1237   0.03598   0.02815  -0.0494   1.0000   0.1623
  -2.500  -0.0945   0.03335   0.02499  -0.0513   1.0000   0.1624
  -2.250  -0.0736   0.03238   0.02397  -0.0519   1.0000   0.1717
  -2.000  -0.0180   0.03009   0.02105  -0.0579   0.9898   0.1821
  -1.750   0.0470   0.02869   0.01924  -0.0653   0.9727   0.2081
  -1.500   0.1072   0.02770   0.01811  -0.0714   0.9543   0.2430
  -1.250   0.1629   0.02654   0.01689  -0.0761   0.9351   0.3252
  -1.000   0.2169   0.02409   0.01504  -0.0806   0.9196   0.4914
  -0.750   0.2724   0.02212   0.01434  -0.0843   0.9021   1.0000
  -0.500   0.3288   0.02231   0.01389  -0.0891   0.8835   1.0000
  -0.250   0.3661   0.02265   0.01385  -0.0906   0.8615   1.0000
   0.000   0.4058   0.02286   0.01373  -0.0922   0.8429   1.0000
   0.250   0.4427   0.02304   0.01363  -0.0930   0.8257   1.0000
   0.500   0.4708   0.02346   0.01384  -0.0927   0.8070   1.0000
   0.750   0.4993   0.02384   0.01403  -0.0924   0.7897   1.0000
   1.000   0.5275   0.02422   0.01424  -0.0919   0.7736   1.0000
   1.250   0.5548   0.02462   0.01451  -0.0912   0.7582   1.0000
   1.500   0.5812   0.02507   0.01483  -0.0905   0.7431   1.0000
   1.750   0.6069   0.02556   0.01521  -0.0896   0.7283   1.0000
   2.000   0.6320   0.02609   0.01564  -0.0887   0.7137   1.0000
   2.250   0.6567   0.02666   0.01613  -0.0878   0.6992   1.0000
   2.500   0.6810   0.02726   0.01668  -0.0868   0.6847   1.0000
   2.750   0.7050   0.02787   0.01724  -0.0858   0.6703   1.0000
   3.000   0.7288   0.02852   0.01785  -0.0848   0.6560   1.0000
   3.250   0.7524   0.02917   0.01847  -0.0837   0.6417   1.0000
   3.500   0.7759   0.02986   0.01918  -0.0827   0.6275   1.0000
   3.750   0.7992   0.03056   0.01988  -0.0816   0.6134   1.0000
   4.000   0.8224   0.03129   0.02061  -0.0805   0.5992   1.0000
   4.250   0.8454   0.03206   0.02140  -0.0795   0.5852   1.0000
   4.500   0.8684   0.03286   0.02227  -0.0784   0.5713   1.0000
   4.750   0.8912   0.03368   0.02313  -0.0773   0.5575   1.0000
   5.000   0.9143   0.03452   0.02401  -0.0763   0.5442   1.0000
   5.250   0.9384   0.03527   0.02480  -0.0752   0.5314   1.0000
   5.500   0.9619   0.03611   0.02574  -0.0742   0.5188   1.0000
   5.750   0.9804   0.03764   0.02741  -0.0733   0.5054   1.0000
   6.000   0.9976   0.03932   0.02925  -0.0725   0.4924   1.0000
   6.250   1.0135   0.04124   0.03133  -0.0718   0.4800   1.0000
   6.500   1.0292   0.04333   0.03362  -0.0711   0.4693   1.0000
   6.750   1.0570   0.04395   0.03431  -0.0701   0.4606   1.0000
   7.000   1.0579   0.04784   0.03847  -0.0698   0.4493   1.0000
   7.250   1.0587   0.05180   0.04262  -0.0695   0.4396   1.0000
   7.500   1.0836   0.05289   0.04385  -0.0685   0.4323   1.0000
   7.750   1.0250   0.06457   0.05565  -0.0713   0.4251   1.0000
   8.000   0.9698   0.07575   0.06672  -0.0753   0.4220   1.0000
   8.250   0.9999   0.07640   0.06756  -0.0737   0.4154   1.0000
   8.500   0.9628   0.08539   0.07648  -0.0770   0.4151   1.0000
   8.750   0.9570   0.09109   0.08223  -0.0786   0.4162   1.0000
   9.250   1.2343   0.05310   0.04535  -0.0555   0.3395   1.0000
   9.500   1.2037   0.06056   0.05305  -0.0552   0.3358   1.0000
   9.750   1.1743   0.06787   0.06046  -0.0555   0.3323   1.0000
  10.000   1.1451   0.07580   0.06840  -0.0568   0.3300   1.0000
  10.250   1.3114   0.04034   0.03274  -0.0408   0.2070   1.0000
  10.500   1.2976   0.04268   0.03500  -0.0378   0.1734   1.0000
  10.750   1.2823   0.04617   0.03839  -0.0362   0.1419   1.0000
  11.000   1.2669   0.05037   0.04243  -0.0358   0.1213   1.0000
  11.250   1.2526   0.05500   0.04692  -0.0362   0.1094   1.0000
  11.500   1.2399   0.05976   0.05164  -0.0368   0.1016   1.0000
  11.750   1.2287   0.06443   0.05624  -0.0375   0.0963   1.0000
  12.000   1.2204   0.06882   0.06064  -0.0378   0.0914   1.0000
  12.250   1.2131   0.07297   0.06470  -0.0380   0.0877   1.0000
  12.500   1.2114   0.07647   0.06828  -0.0375   0.0841   1.0000
  12.750   1.2122   0.07970   0.07162  -0.0368   0.0807   1.0000
  13.000   1.2160   0.08243   0.07434  -0.0356   0.0775   1.0000
  13.250   1.2253   0.08453   0.07642  -0.0334   0.0743   1.0000
  13.500   1.2246   0.08862   0.08081  -0.0335   0.0725   1.0000
  13.750   1.2209   0.09325   0.08571  -0.0342   0.0711   1.0000
  14.000   1.2135   0.09856   0.09127  -0.0355   0.0703   1.0000
  14.250   1.2006   0.10499   0.09797  -0.0380   0.0702   1.0000
  14.500   1.1810   0.11296   0.10619  -0.0419   0.0709   1.0000
  14.750   1.1567   0.12241   0.11587  -0.0471   0.0723   1.0000
  15.000   1.1333   0.13242   0.12602  -0.0526   0.0738   1.0000
  15.250   1.1146   0.14199   0.13566  -0.0576   0.0750   1.0000
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