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SA7025 (sa7025-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 50,000
Max Cl/Cd: 38.07 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7025-il-50000.txt
Download as CSV file: xf-sa7025-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7025                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3759   0.10109   0.09483  -0.0248   1.0000   0.1948
  -7.250  -0.3600   0.09650   0.09026  -0.0229   1.0000   0.2064
  -7.000  -0.3863   0.09690   0.09087  -0.0221   1.0000   0.2090
  -6.750  -0.3748   0.09290   0.08690  -0.0192   1.0000   0.2211
  -6.500  -0.3731   0.08997   0.08405  -0.0172   1.0000   0.2305
  -6.250  -0.3957   0.08990   0.08414  -0.0184   1.0000   0.2372
  -6.000  -0.3911   0.08671   0.08101  -0.0155   1.0000   0.2504
  -5.750  -0.3872   0.08362   0.07799  -0.0127   1.0000   0.2620
  -5.500  -0.3880   0.08108   0.07552  -0.0110   1.0000   0.2733
  -5.250  -0.3899   0.07867   0.07320  -0.0094   1.0000   0.2870
  -5.000  -0.3906   0.07628   0.07088  -0.0079   1.0000   0.3019
  -4.750  -0.3963   0.07453   0.06920  -0.0089   1.0000   0.3227
  -4.500  -0.3912   0.07139   0.06609  -0.0048   1.0000   0.3396
  -4.250  -0.3912   0.06918   0.06394  -0.0034   1.0000   0.3657
  -4.000  -0.3872   0.06656   0.06138   0.0006   1.0000   0.3899
  -3.750  -0.3869   0.06417   0.05907   0.0038   1.0000   0.4227
  -3.500  -0.3843   0.06168   0.05665   0.0089   1.0000   0.4535
  -3.250  -0.2238   0.04246   0.03500  -0.0519   1.0000   0.1380
  -3.000  -0.1916   0.03820   0.03025  -0.0539   1.0000   0.1208
  -2.750  -0.1560   0.03465   0.02582  -0.0559   1.0000   0.1097
  -2.500  -0.1269   0.03215   0.02287  -0.0565   1.0000   0.1082
  -2.250  -0.0978   0.03027   0.02040  -0.0567   1.0000   0.1104
  -2.000  -0.0715   0.02847   0.01838  -0.0567   1.0000   0.1151
  -1.750  -0.0452   0.02705   0.01664  -0.0562   1.0000   0.1199
  -1.500  -0.0198   0.02581   0.01515  -0.0554   1.0000   0.1280
  -1.250   0.0059   0.02484   0.01405  -0.0548   1.0000   0.1532
  -1.000   0.0384   0.02050   0.01280  -0.0541   1.0000   0.6479
  -0.750   0.0543   0.01998   0.01194  -0.0516   1.0000   1.0000
  -0.500   0.0760   0.02043   0.01186  -0.0513   1.0000   1.0000
  -0.250   0.0968   0.02093   0.01193  -0.0510   1.0000   1.0000
   0.000   0.1170   0.02148   0.01215  -0.0508   1.0000   1.0000
   0.250   0.1367   0.02208   0.01248  -0.0506   1.0000   1.0000
   0.500   0.1559   0.02274   0.01290  -0.0504   1.0000   1.0000
   0.750   0.1746   0.02345   0.01341  -0.0502   1.0000   1.0000
   1.000   0.1928   0.02423   0.01400  -0.0502   1.0000   1.0000
   1.250   0.2153   0.02516   0.01477  -0.0510   0.9976   1.0000
   1.500   0.2682   0.02670   0.01611  -0.0574   0.9802   1.0000
   1.750   0.3162   0.02800   0.01726  -0.0626   0.9619   1.0000
   2.000   0.3659   0.02925   0.01841  -0.0678   0.9441   1.0000
   2.250   0.4072   0.03024   0.01935  -0.0713   0.9248   1.0000
   2.500   0.4494   0.03115   0.02025  -0.0748   0.9059   1.0000
   2.750   0.4975   0.03197   0.02107  -0.0788   0.8879   1.0000
   3.000   0.5299   0.03265   0.02179  -0.0802   0.8674   1.0000
   3.250   0.5738   0.03319   0.02243  -0.0831   0.8486   1.0000
   3.500   0.6115   0.03365   0.02297  -0.0848   0.8289   1.0000
   3.750   0.6509   0.03394   0.02337  -0.0865   0.8090   1.0000
   4.000   0.7032   0.03370   0.02331  -0.0894   0.7914   1.0000
   4.250   0.7319   0.03398   0.02377  -0.0891   0.7692   1.0000
   4.500   0.7842   0.03319   0.02321  -0.0910   0.7514   1.0000
   4.750   0.8175   0.03301   0.02320  -0.0905   0.7298   1.0000
   5.000   0.8655   0.03184   0.02234  -0.0910   0.7106   1.0000
   5.250   0.9003   0.03131   0.02201  -0.0900   0.6875   1.0000
   5.500   0.9442   0.03008   0.02099  -0.0894   0.6648   1.0000
   5.750   0.9838   0.02909   0.02017  -0.0883   0.6392   1.0000
   6.000   1.0136   0.02880   0.02009  -0.0865   0.6101   1.0000
   6.250   1.0399   0.02881   0.02022  -0.0845   0.5785   1.0000
   6.500   1.0678   0.02876   0.02023  -0.0824   0.5454   1.0000
   6.750   1.0931   0.02896   0.02046  -0.0803   0.5107   1.0000
   7.000   1.1166   0.02933   0.02090  -0.0781   0.4742   1.0000
   7.250   1.1365   0.02999   0.02158  -0.0756   0.4362   1.0000
   7.500   1.1559   0.03071   0.02226  -0.0731   0.3965   1.0000
   7.750   1.1729   0.03157   0.02303  -0.0704   0.3549   1.0000
   8.000   1.1872   0.03260   0.02394  -0.0676   0.3117   1.0000
   8.250   1.1993   0.03392   0.02506  -0.0646   0.2674   1.0000
   8.500   1.2090   0.03554   0.02634  -0.0615   0.2224   1.0000
   8.750   1.2139   0.03766   0.02828  -0.0581   0.1799   1.0000
   9.000   1.2215   0.04035   0.03068  -0.0551   0.1417   1.0000
   9.250   1.2256   0.04304   0.03335  -0.0521   0.1139   1.0000
   9.500   1.2323   0.04590   0.03638  -0.0495   0.0948   1.0000
   9.750   1.2476   0.04984   0.04058  -0.0479   0.0844   1.0000
  10.000   1.2668   0.05424   0.04496  -0.0471   0.0770   1.0000
  10.250   1.2659   0.05800   0.04941  -0.0442   0.0746   1.0000
  10.500   1.2620   0.06197   0.05389  -0.0414   0.0724   1.0000
  10.750   1.2550   0.06589   0.05821  -0.0389   0.0709   1.0000
  11.000   1.2420   0.06977   0.06242  -0.0362   0.0703   1.0000
  11.250   1.2234   0.07388   0.06684  -0.0338   0.0705   1.0000
  11.500   1.2007   0.07851   0.07174  -0.0325   0.0713   1.0000
  11.750   1.1765   0.08375   0.07723  -0.0325   0.0724   1.0000
  12.000   1.1525   0.08967   0.08334  -0.0338   0.0737   1.0000
  12.250   1.1307   0.09611   0.08992  -0.0361   0.0750   1.0000
  12.500   1.1111   0.10306   0.09696  -0.0392   0.0761   1.0000
  12.750   1.0946   0.11039   0.10435  -0.0427   0.0769   1.0000
  13.000   1.0070   0.13752   0.13139  -0.0653   0.0995   1.0000
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