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SA7025 (sa7025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.38 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7025-il-1000000-n5.txt
Download as CSV file: xf-sa7025-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3967   0.13436   0.13262  -0.0208   1.0000   0.0030
 -11.750  -0.3910   0.13139   0.12966  -0.0220   1.0000   0.0041
 -11.500  -0.3864   0.12771   0.12599  -0.0231   1.0000   0.0039
 -11.250  -0.3793   0.12536   0.12364  -0.0240   1.0000   0.0049
 -11.000  -0.3753   0.12178   0.12007  -0.0251   1.0000   0.0044
 -10.750  -0.3699   0.11875   0.11704  -0.0260   1.0000   0.0048
 -10.500  -0.3635   0.11544   0.11374  -0.0275   1.0000   0.0059
 -10.250  -0.2681   0.10204   0.10051  -0.0339   0.9995   0.0061
  -9.750  -0.2550   0.09387   0.09234  -0.0379   0.9915   0.0061
  -9.500  -0.2479   0.08958   0.08804  -0.0402   0.9880   0.0061
  -9.250  -0.2406   0.08522   0.08369  -0.0426   0.9849   0.0061
  -9.000  -0.2332   0.08077   0.07924  -0.0451   0.9811   0.0061
  -8.750  -0.2263   0.07638   0.07485  -0.0475   0.9762   0.0061
  -8.500  -0.3243   0.08924   0.08766  -0.0378   0.9900   0.0061
  -8.250  -0.3112   0.08471   0.08313  -0.0423   0.9855   0.0061
  -8.000  -0.2957   0.08019   0.07861  -0.0475   0.9817   0.0061
  -7.750  -0.2845   0.07523   0.07365  -0.0531   0.9750   0.0051
  -7.500  -0.2688   0.07001   0.06842  -0.0602   0.9650   0.0047
  -7.250  -0.2596   0.06470   0.06307  -0.0668   0.9505   0.0043
  -7.000  -0.2575   0.05765   0.05597  -0.0740   0.9344   0.0039
  -6.750  -0.2540   0.04845   0.04665  -0.0826   0.9205   0.0037
  -6.500  -0.2421   0.04077   0.03878  -0.0884   0.9112   0.0038
  -6.250  -0.2290   0.03210   0.02977  -0.0924   0.9027   0.0038
  -6.000  -0.2123   0.02530   0.02256  -0.0939   0.8957   0.0040
  -5.750  -0.1913   0.02172   0.01864  -0.0942   0.8896   0.0043
  -5.500  -0.1685   0.01863   0.01517  -0.0943   0.8837   0.0047
  -5.250  -0.1442   0.01641   0.01261  -0.0942   0.8775   0.0049
  -5.000  -0.1188   0.01470   0.01059  -0.0940   0.8720   0.0051
  -4.750  -0.0926   0.01334   0.00897  -0.0938   0.8659   0.0053
  -4.500  -0.0660   0.01250   0.00794  -0.0937   0.8602   0.0055
  -4.250  -0.0388   0.01182   0.00710  -0.0935   0.8534   0.0058
  -4.000  -0.0121   0.01092   0.00601  -0.0933   0.8466   0.0058
  -3.750   0.0150   0.01006   0.00500  -0.0931   0.8388   0.0058
  -3.500   0.0420   0.00937   0.00417  -0.0929   0.8309   0.0058
  -3.250   0.0692   0.00879   0.00348  -0.0927   0.8219   0.0058
  -3.000   0.0967   0.00833   0.00291  -0.0925   0.8128   0.0059
  -2.750   0.1241   0.00797   0.00244  -0.0924   0.8030   0.0059
  -2.500   0.1517   0.00770   0.00207  -0.0922   0.7917   0.0061
  -2.250   0.1792   0.00748   0.00177  -0.0921   0.7781   0.0063
  -2.000   0.2067   0.00721   0.00135  -0.0919   0.7621   0.0076
  -1.750   0.2341   0.00712   0.00117  -0.0917   0.7443   0.0088
  -1.500   0.2615   0.00708   0.00103  -0.0915   0.7266   0.0100
  -1.250   0.2888   0.00702   0.00092  -0.0914   0.7094   0.0181
  -1.000   0.3160   0.00683   0.00084  -0.0913   0.6915   0.0709
  -0.750   0.3431   0.00668   0.00079  -0.0913   0.6736   0.1329
  -0.250   0.3967   0.00625   0.00079  -0.0912   0.6355   0.3378
   0.000   0.4235   0.00621   0.00081  -0.0911   0.6140   0.4012
   0.250   0.4503   0.00614   0.00084  -0.0910   0.5930   0.4730
   0.500   0.4771   0.00610   0.00088  -0.0909   0.5736   0.5353
   0.750   0.5039   0.00602   0.00093  -0.0908   0.5556   0.6118
   1.000   0.5295   0.00581   0.00101  -0.0904   0.5374   0.7396
   1.250   0.5495   0.00552   0.00110  -0.0885   0.5193   0.9025
   1.500   0.5827   0.00555   0.00113  -0.0896   0.4984   1.0000
   1.750   0.6093   0.00572   0.00119  -0.0894   0.4775   1.0000
   2.000   0.6361   0.00589   0.00126  -0.0892   0.4576   1.0000
   2.250   0.6627   0.00608   0.00135  -0.0890   0.4364   1.0000
   2.500   0.6893   0.00625   0.00144  -0.0889   0.4177   1.0000
   2.750   0.7160   0.00643   0.00153  -0.0887   0.3986   1.0000
   3.000   0.7424   0.00663   0.00164  -0.0885   0.3796   1.0000
   3.250   0.7687   0.00684   0.00176  -0.0882   0.3573   1.0000
   3.500   0.7947   0.00708   0.00191  -0.0880   0.3340   1.0000
   3.750   0.8208   0.00732   0.00206  -0.0878   0.3130   1.0000
   4.000   0.8470   0.00754   0.00221  -0.0875   0.2960   1.0000
   4.250   0.8731   0.00777   0.00237  -0.0873   0.2765   1.0000
   4.500   0.8974   0.00820   0.00262  -0.0868   0.2374   1.0000
   4.750   0.9216   0.00863   0.00287  -0.0863   0.2017   1.0000
   5.000   0.9459   0.00905   0.00314  -0.0859   0.1694   1.0000
   5.250   0.9701   0.00948   0.00342  -0.0854   0.1397   1.0000
   5.500   0.9929   0.01006   0.00378  -0.0848   0.1009   1.0000
   5.750   1.0143   0.01081   0.00428  -0.0839   0.0545   1.0000
   6.000   1.0354   0.01159   0.00483  -0.0830   0.0180   1.0000
   6.250   1.0587   0.01210   0.00528  -0.0823   0.0055   1.0000
   6.500   1.0832   0.01244   0.00563  -0.0818   0.0037   1.0000
   6.750   1.1078   0.01277   0.00600  -0.0813   0.0033   1.0000
   7.000   1.1320   0.01313   0.00639  -0.0808   0.0030   1.0000
   7.250   1.1555   0.01357   0.00689  -0.0802   0.0026   1.0000
   7.500   1.1785   0.01403   0.00742  -0.0795   0.0023   1.0000
   7.750   1.2006   0.01461   0.00808  -0.0786   0.0022   1.0000
   8.000   1.2215   0.01529   0.00885  -0.0775   0.0020   1.0000
   8.250   1.2419   0.01599   0.00963  -0.0764   0.0020   1.0000
   8.500   1.2625   0.01663   0.01035  -0.0753   0.0020   1.0000
   8.750   1.2821   0.01734   0.01114  -0.0741   0.0019   1.0000
   9.000   1.3006   0.01811   0.01199  -0.0728   0.0019   1.0000
   9.250   1.3179   0.01895   0.01295  -0.0713   0.0019   1.0000
   9.500   1.3337   0.01986   0.01396  -0.0696   0.0019   1.0000
   9.750   1.3501   0.02066   0.01484  -0.0680   0.0019   1.0000
  10.000   1.3647   0.02153   0.01580  -0.0662   0.0018   1.0000
  10.250   1.3774   0.02233   0.01668  -0.0640   0.0018   1.0000
  10.500   1.3874   0.02323   0.01767  -0.0614   0.0017   1.0000
  10.750   1.3960   0.02422   0.01877  -0.0588   0.0017   1.0000
  11.000   1.4036   0.02533   0.01998  -0.0562   0.0016   1.0000
  11.250   1.4085   0.02668   0.02145  -0.0534   0.0016   1.0000
  11.500   1.4118   0.02822   0.02312  -0.0507   0.0016   1.0000
  11.750   1.4177   0.02959   0.02462  -0.0485   0.0016   1.0000
  12.000   1.4190   0.03144   0.02660  -0.0461   0.0016   1.0000
  12.250   1.4205   0.03334   0.02864  -0.0440   0.0015   1.0000
  12.500   1.4200   0.03554   0.03098  -0.0421   0.0015   1.0000
  12.750   1.4194   0.03785   0.03343  -0.0405   0.0015   1.0000
  13.000   1.4178   0.04041   0.03613  -0.0392   0.0015   1.0000
  13.250   1.4159   0.04313   0.03899  -0.0383   0.0014   1.0000
  13.500   1.4128   0.04615   0.04215  -0.0378   0.0014   1.0000
  13.750   1.4052   0.04995   0.04612  -0.0376   0.0014   1.0000
  14.000   1.3988   0.05384   0.05016  -0.0380   0.0014   1.0000
  14.250   1.3917   0.05809   0.05455  -0.0390   0.0014   1.0000
  14.500   1.3812   0.06314   0.05976  -0.0404   0.0014   1.0000
  14.750   1.3700   0.06867   0.06545  -0.0425   0.0014   1.0000
  15.000   1.3595   0.07443   0.07135  -0.0451   0.0013   1.0000
  15.250   1.3456   0.08113   0.07821  -0.0483   0.0013   1.0000
  15.500   1.3293   0.08866   0.08591  -0.0521   0.0014   1.0000
  15.750   1.3139   0.09637   0.09376  -0.0563   0.0014   1.0000
  16.000   1.3002   0.10408   0.10160  -0.0606   0.0013   1.0000
  16.250   1.2847   0.11245   0.11011  -0.0654   0.0013   1.0000
  16.500   1.2646   0.12215   0.11995  -0.0709   0.0014   1.0000
  16.750   1.2485   0.13123   0.12916  -0.0762   0.0014   1.0000
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