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SA7025 (sa7025-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 100,000
Max Cl/Cd: 60.57 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7025-il-100000.txt
Download as CSV file: xf-sa7025-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3470   0.09400   0.08940  -0.0307   1.0000   0.0779
  -7.500  -0.3554   0.09224   0.08774  -0.0297   1.0000   0.0801
  -7.250  -0.3708   0.09119   0.08680  -0.0280   1.0000   0.0816
  -7.000  -0.3873   0.09008   0.08580  -0.0284   1.0000   0.0827
  -6.750  -0.3993   0.08854   0.08433  -0.0332   1.0000   0.0835
  -6.500  -0.4021   0.08472   0.08057  -0.0337   1.0000   0.0844
  -6.250  -0.3965   0.08154   0.07744  -0.0260   1.0000   0.0868
  -6.000  -0.3957   0.07912   0.07506  -0.0245   1.0000   0.0895
  -5.750  -0.3952   0.07641   0.07237  -0.0256   1.0000   0.0933
  -5.500  -0.3877   0.07212   0.06794  -0.0372   1.0000   0.0981
  -5.250  -0.3863   0.06928   0.06523  -0.0313   1.0000   0.1001
  -5.000  -0.3803   0.06679   0.06277  -0.0298   1.0000   0.1040
  -4.750  -0.3631   0.06223   0.05802  -0.0373   1.0000   0.1129
  -4.500  -0.3427   0.05985   0.05533  -0.0419   1.0000   0.1251
  -4.250  -0.3373   0.05595   0.05164  -0.0389   1.0000   0.1275
  -4.000  -0.3250   0.05355   0.04925  -0.0379   1.0000   0.1343
  -3.750  -0.3071   0.05036   0.04593  -0.0396   1.0000   0.1454
  -3.500  -0.2875   0.04751   0.04298  -0.0411   1.0000   0.1589
  -3.250  -0.2635   0.04484   0.04008  -0.0439   1.0000   0.1829
  -3.000  -0.2484   0.04274   0.03805  -0.0427   1.0000   0.2005
  -2.750  -0.1639   0.03106   0.02438  -0.0541   1.0000   0.0795
  -2.500  -0.1305   0.02777   0.02032  -0.0546   1.0000   0.0665
  -2.250  -0.0896   0.02510   0.01698  -0.0566   0.9969   0.0606
  -2.000  -0.0451   0.02338   0.01473  -0.0591   0.9914   0.0588
  -1.750  -0.0020   0.02204   0.01320  -0.0618   0.9853   0.0606
  -1.500   0.0390   0.02114   0.01224  -0.0642   0.9782   0.0656
  -1.250   0.0829   0.02038   0.01150  -0.0673   0.9715   0.0850
  -1.000   0.1166   0.01737   0.01104  -0.0684   0.9669   0.6592
  -0.750   0.1631   0.01701   0.01080  -0.0714   0.9582   1.0000
  -0.500   0.2024   0.01732   0.01077  -0.0739   0.9474   1.0000
  -0.250   0.2431   0.01762   0.01080  -0.0766   0.9372   1.0000
   0.000   0.2911   0.01788   0.01081  -0.0806   0.9292   1.0000
   0.250   0.3275   0.01804   0.01081  -0.0823   0.9175   1.0000
   0.500   0.3651   0.01817   0.01081  -0.0842   0.9060   1.0000
   0.750   0.4047   0.01824   0.01076  -0.0863   0.8952   1.0000
   1.000   0.4557   0.01811   0.01054  -0.0903   0.8880   1.0000
   1.250   0.4922   0.01805   0.01043  -0.0917   0.8759   1.0000
   1.500   0.5282   0.01794   0.01029  -0.0928   0.8641   1.0000
   1.750   0.5643   0.01776   0.01010  -0.0937   0.8526   1.0000
   2.000   0.6011   0.01749   0.00982  -0.0946   0.8415   1.0000
   2.250   0.6418   0.01702   0.00935  -0.0959   0.8326   1.0000
   2.500   0.6736   0.01672   0.00909  -0.0958   0.8192   1.0000
   2.750   0.7051   0.01639   0.00878  -0.0954   0.8053   1.0000
   3.000   0.7333   0.01617   0.00858  -0.0946   0.7890   1.0000
   3.250   0.7616   0.01595   0.00839  -0.0938   0.7719   1.0000
   3.500   0.7908   0.01570   0.00820  -0.0930   0.7545   1.0000
   3.750   0.8207   0.01545   0.00795  -0.0924   0.7368   1.0000
   4.000   0.8465   0.01542   0.00793  -0.0912   0.7146   1.0000
   4.250   0.8742   0.01537   0.00785  -0.0903   0.6927   1.0000
   4.500   0.9002   0.01544   0.00795  -0.0892   0.6684   1.0000
   4.750   0.9250   0.01561   0.00811  -0.0881   0.6424   1.0000
   5.000   0.9495   0.01584   0.00831  -0.0869   0.6155   1.0000
   5.250   0.9735   0.01612   0.00856  -0.0857   0.5875   1.0000
   5.500   0.9969   0.01646   0.00890  -0.0844   0.5586   1.0000
   5.750   1.0197   0.01684   0.00924  -0.0831   0.5290   1.0000
   6.000   1.0417   0.01729   0.00965  -0.0817   0.4985   1.0000
   6.250   1.0629   0.01779   0.01015  -0.0803   0.4668   1.0000
   6.500   1.0836   0.01833   0.01066  -0.0788   0.4346   1.0000
   6.750   1.1036   0.01894   0.01123  -0.0773   0.4024   1.0000
   7.000   1.1219   0.01957   0.01188  -0.0756   0.3670   1.0000
   7.250   1.1395   0.02030   0.01252  -0.0738   0.3324   1.0000
   7.500   1.1558   0.02109   0.01330  -0.0719   0.2955   1.0000
   7.750   1.1704   0.02198   0.01414  -0.0699   0.2578   1.0000
   8.000   1.1823   0.02294   0.01500  -0.0676   0.2155   1.0000
   8.250   1.1914   0.02413   0.01597  -0.0652   0.1685   1.0000
   8.500   1.1978   0.02585   0.01736  -0.0627   0.1086   1.0000
   8.750   1.1948   0.02884   0.01992  -0.0587   0.0630   1.0000
   9.000   1.1975   0.03132   0.02239  -0.0552   0.0488   1.0000
   9.250   1.2020   0.03378   0.02478  -0.0522   0.0426   1.0000
   9.500   1.2190   0.03632   0.02749  -0.0504   0.0388   1.0000
   9.750   1.2408   0.03907   0.03042  -0.0495   0.0361   1.0000
  10.000   1.2608   0.04200   0.03352  -0.0486   0.0340   1.0000
  10.250   1.2813   0.04672   0.03837  -0.0485   0.0317   1.0000
  10.500   1.2865   0.04970   0.04177  -0.0460   0.0307   1.0000
  10.750   1.2884   0.05264   0.04511  -0.0433   0.0302   1.0000
  11.000   1.2845   0.05584   0.04869  -0.0403   0.0299   1.0000
  11.250   1.2773   0.05942   0.05261  -0.0375   0.0300   1.0000
  11.500   1.2661   0.06315   0.05666  -0.0350   0.0302   1.0000
  11.750   1.2524   0.06709   0.06089  -0.0331   0.0303   1.0000
  12.000   1.2363   0.07141   0.06548  -0.0319   0.0305   1.0000
  12.250   1.2194   0.07609   0.07040  -0.0315   0.0307   1.0000
  12.500   1.2014   0.08128   0.07581  -0.0321   0.0309   1.0000
  12.750   1.1819   0.08697   0.08170  -0.0335   0.0311   1.0000
  13.000   1.1638   0.09335   0.08824  -0.0357   0.0313   1.0000
  13.250   1.1471   0.09935   0.09446  -0.0386   0.0316   1.0000
  13.500   1.1282   0.10575   0.10105  -0.0428   0.0319   1.0000
  13.750   1.1055   0.11379   0.10929  -0.0490   0.0323   1.0000
  14.000   0.8807   0.13002   0.12619  -0.0568   0.0408   1.0000
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