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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 50,000
Max Cl/Cd: 35.86 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa25-il-50000-n5.txt
Download as CSV file: xf-usa25-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 25 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3379   0.10816   0.10164  -0.0256   1.0000   0.1038
  -7.750  -0.3518   0.10718   0.10079  -0.0248   1.0000   0.1042
  -7.500  -0.3604   0.10566   0.09936  -0.0251   1.0000   0.1044
  -7.250  -0.3669   0.10402   0.09779  -0.0256   1.0000   0.1047
  -7.000  -0.3607   0.09936   0.09320  -0.0235   1.0000   0.1054
  -6.750  -0.3548   0.09538   0.08925  -0.0212   1.0000   0.1068
  -6.500  -0.3528   0.09249   0.08641  -0.0195   1.0000   0.1089
  -6.250  -0.3532   0.09011   0.08408  -0.0184   1.0000   0.1121
  -6.000  -0.3554   0.08823   0.08223  -0.0185   1.0000   0.1160
  -5.750  -0.3574   0.08738   0.08134  -0.0212   1.0000   0.1186
  -5.250  -0.3503   0.08078   0.07481  -0.0190   1.0000   0.1206
  -5.000  -0.3455   0.07782   0.07188  -0.0177   1.0000   0.1220
  -4.750  -0.3304   0.07461   0.06863  -0.0191   0.9971   0.1235
  -4.500  -0.2798   0.06857   0.06195  -0.0314   0.9871   0.0899
  -4.250  -0.2532   0.06436   0.05771  -0.0337   0.9789   0.0885
  -4.000  -0.2222   0.06052   0.05371  -0.0372   0.9697   0.0868
  -3.750  -0.1883   0.05662   0.04961  -0.0411   0.9605   0.0827
  -3.250  -0.1148   0.04830   0.04037  -0.0488   0.9388   0.0750
  -3.000  -0.0827   0.04532   0.03712  -0.0508   0.9273   0.0746
  -2.750  -0.0497   0.04282   0.03446  -0.0529   0.9156   0.0770
  -2.500  -0.0152   0.04077   0.03222  -0.0548   0.9034   0.0795
  -2.250   0.0179   0.03824   0.02937  -0.0561   0.8895   0.0800
  -2.000   0.0518   0.03572   0.02647  -0.0572   0.8754   0.0803
  -1.750   0.0867   0.03340   0.02378  -0.0583   0.8608   0.0813
  -1.500   0.1227   0.03120   0.02120  -0.0593   0.8458   0.0831
  -1.250   0.1601   0.02907   0.01862  -0.0603   0.8301   0.0860
  -1.000   0.1969   0.02740   0.01659  -0.0613   0.8116   0.0919
  -0.750   0.2366   0.02636   0.01537  -0.0629   0.7911   0.1015
  -0.500   0.2846   0.02514   0.01383  -0.0657   0.7705   0.1152
  -0.250   0.3269   0.02426   0.01271  -0.0675   0.7458   0.1365
   0.000   0.3646   0.02400   0.01229  -0.0689   0.7213   0.1679
   0.250   0.3980   0.02384   0.01199  -0.0697   0.6965   0.1989
   0.500   0.4344   0.02346   0.01136  -0.0708   0.6752   0.2180
   0.750   0.4667   0.02316   0.01082  -0.0711   0.6557   0.2277
   1.000   0.4967   0.02300   0.01045  -0.0712   0.6394   0.2398
   1.250   0.5246   0.02288   0.01020  -0.0710   0.6256   0.2551
   1.500   0.5518   0.02278   0.00998  -0.0708   0.6137   0.2708
   1.750   0.5771   0.02273   0.00988  -0.0702   0.6023   0.2888
   2.000   0.6016   0.02264   0.00983  -0.0697   0.5924   0.3177
   2.250   0.6234   0.02193   0.00973  -0.0688   0.5844   0.4517
   2.750   0.7402   0.02221   0.01034  -0.0807   0.5645   1.0000
   3.000   0.7651   0.02262   0.01063  -0.0802   0.5571   1.0000
   3.250   0.7906   0.02304   0.01094  -0.0797   0.5505   1.0000
   3.500   0.8136   0.02351   0.01138  -0.0789   0.5435   1.0000
   4.000   0.8606   0.02448   0.01229  -0.0775   0.5308   1.0000
   4.250   0.8850   0.02497   0.01277  -0.0769   0.5247   1.0000
   4.500   0.9070   0.02553   0.01335  -0.0759   0.5184   1.0000
   4.750   0.9284   0.02609   0.01396  -0.0749   0.5116   1.0000
   5.000   0.9527   0.02662   0.01446  -0.0742   0.5052   1.0000
   5.250   0.9707   0.02722   0.01517  -0.0726   0.4966   1.0000
   5.500   0.9929   0.02772   0.01568  -0.0715   0.4882   1.0000
   5.750   1.0123   0.02826   0.01628  -0.0700   0.4788   1.0000
   6.000   1.0311   0.02885   0.01697  -0.0685   0.4700   1.0000
   6.250   1.0532   0.02937   0.01753  -0.0674   0.4617   1.0000
   6.500   1.0699   0.03008   0.01839  -0.0656   0.4535   1.0000
   6.750   1.0921   0.03066   0.01905  -0.0646   0.4461   1.0000
   7.000   1.1079   0.03144   0.02004  -0.0628   0.4379   1.0000
   7.250   1.1295   0.03203   0.02074  -0.0617   0.4302   1.0000
   7.500   1.1436   0.03288   0.02180  -0.0596   0.4216   1.0000
   7.750   1.1661   0.03343   0.02244  -0.0586   0.4136   1.0000
   8.000   1.1765   0.03441   0.02368  -0.0561   0.4044   1.0000
   8.250   1.2013   0.03488   0.02427  -0.0554   0.3967   1.0000
   8.500   1.2068   0.03605   0.02576  -0.0523   0.3870   1.0000
   8.750   1.2228   0.03668   0.02655  -0.0504   0.3774   1.0000
   9.000   1.2369   0.03676   0.02674  -0.0478   0.3641   1.0000
   9.250   1.2437   0.03687   0.02697  -0.0443   0.3491   1.0000
   9.500   1.2498   0.03709   0.02739  -0.0408   0.3352   1.0000
   9.750   1.2504   0.03804   0.02859  -0.0371   0.3233   1.0000
  10.000   1.2520   0.03895   0.02971  -0.0335   0.3123   1.0000
  10.250   1.2520   0.03963   0.03053  -0.0296   0.3003   1.0000
  10.500   1.2502   0.04039   0.03139  -0.0258   0.2868   1.0000
  10.750   1.2460   0.04140   0.03249  -0.0221   0.2716   1.0000
  11.000   1.2446   0.04264   0.03381  -0.0192   0.2587   1.0000
  11.250   1.2423   0.04414   0.03539  -0.0166   0.2458   1.0000
  11.500   1.2381   0.04600   0.03730  -0.0144   0.2325   1.0000
  11.750   1.2305   0.04839   0.03972  -0.0126   0.2181   1.0000
  12.000   1.2202   0.05137   0.04276  -0.0113   0.2033   1.0000
  12.250   1.2077   0.05495   0.04636  -0.0107   0.1882   1.0000
  12.500   1.1953   0.05890   0.05032  -0.0107   0.1744   1.0000
  12.750   1.1825   0.06329   0.05476  -0.0112   0.1606   1.0000
  13.000   1.1696   0.06800   0.05954  -0.0121   0.1466   1.0000
  13.250   1.1562   0.07309   0.06477  -0.0135   0.1307   1.0000
  13.500   1.1431   0.07824   0.06998  -0.0148   0.1099   1.0000
  13.750   1.1310   0.08308   0.07471  -0.0160   0.0919   1.0000
  14.000   1.1178   0.08818   0.07966  -0.0174   0.0796   1.0000
  14.250   1.1053   0.09340   0.08479  -0.0189   0.0708   1.0000
  14.500   1.0946   0.09852   0.08990  -0.0204   0.0635   1.0000
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