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SA7025 (sa7025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.74 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7025-il-1000000.txt
Download as CSV file: xf-sa7025-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3434   0.09401   0.09243  -0.0322   1.0000   0.0076
  -8.500  -0.3482   0.09173   0.09019  -0.0310   1.0000   0.0080
  -8.250  -0.3463   0.08877   0.08726  -0.0319   0.9992   0.0080
  -8.000  -0.3306   0.08422   0.08270  -0.0373   0.9967   0.0084
  -7.750  -0.3141   0.07963   0.07811  -0.0432   0.9926   0.0086
  -7.500  -0.2960   0.07508   0.07357  -0.0493   0.9880   0.0088
  -7.250  -0.2738   0.06961   0.06810  -0.0580   0.9846   0.0089
  -7.000  -0.2487   0.06386   0.06233  -0.0676   0.9808   0.0089
  -6.750  -0.2241   0.05775   0.05619  -0.0772   0.9742   0.0089
  -6.500  -0.2015   0.05087   0.04923  -0.0863   0.9654   0.0089
  -6.250  -0.1847   0.04479   0.04302  -0.0914   0.9559   0.0089
  -6.000  -0.1837   0.03367   0.03153  -0.0967   0.9432   0.0096
  -5.750  -0.1653   0.03205   0.02981  -0.0973   0.9367   0.0101
  -5.500  -0.1460   0.02910   0.02666  -0.0977   0.9307   0.0106
  -5.250  -0.1247   0.02619   0.02352  -0.0981   0.9248   0.0115
  -5.000  -0.1019   0.02327   0.02032  -0.0980   0.9191   0.0125
  -4.750  -0.0740   0.02310   0.01997  -0.0973   0.9147   0.0139
  -4.500  -0.0549   0.01742   0.01367  -0.0976   0.9083   0.0152
  -4.250  -0.0301   0.01627   0.01240  -0.0975   0.9033   0.0162
  -4.000  -0.0041   0.01525   0.01123  -0.0973   0.8980   0.0173
  -3.750   0.0227   0.01437   0.01019  -0.0970   0.8921   0.0192
  -3.500   0.0492   0.01310   0.00861  -0.0967   0.8870   0.0229
  -3.250   0.0769   0.00958   0.00469  -0.0953   0.8809   0.0112
  -3.000   0.1038   0.00868   0.00365  -0.0949   0.8751   0.0110
  -2.750   0.1312   0.00816   0.00305  -0.0946   0.8686   0.0119
  -2.500   0.1586   0.00777   0.00257  -0.0944   0.8619   0.0125
  -2.250   0.1863   0.00745   0.00218  -0.0942   0.8545   0.0130
  -2.000   0.2139   0.00721   0.00186  -0.0940   0.8467   0.0135
  -1.750   0.2417   0.00702   0.00162  -0.0939   0.8376   0.0140
  -1.500   0.2696   0.00681   0.00131  -0.0937   0.8288   0.0144
  -1.250   0.2974   0.00669   0.00109  -0.0935   0.8191   0.0169
  -1.000   0.3248   0.00624   0.00095  -0.0935   0.8083   0.1163
  -0.750   0.3519   0.00583   0.00089  -0.0936   0.7967   0.2508
  -0.500   0.3789   0.00555   0.00086  -0.0935   0.7834   0.3574
  -0.250   0.4052   0.00516   0.00088  -0.0934   0.7681   0.5245
   0.000   0.4263   0.00437   0.00097  -0.0920   0.7512   0.8382
   0.250   0.4590   0.00416   0.00092  -0.0927   0.7328   1.0000
   0.500   0.4858   0.00427   0.00092  -0.0924   0.7136   1.0000
   1.000   0.5394   0.00451   0.00095  -0.0919   0.6752   1.0000
   1.250   0.5662   0.00465   0.00098  -0.0916   0.6552   1.0000
   1.500   0.5929   0.00479   0.00102  -0.0914   0.6344   1.0000
   1.750   0.6195   0.00495   0.00107  -0.0911   0.6130   1.0000
   2.000   0.6462   0.00510   0.00113  -0.0909   0.5912   1.0000
   2.500   0.6994   0.00544   0.00129  -0.0905   0.5482   1.0000
   2.750   0.7259   0.00562   0.00138  -0.0902   0.5269   1.0000
   3.000   0.7525   0.00580   0.00147  -0.0900   0.5051   1.0000
   3.250   0.7787   0.00602   0.00160  -0.0897   0.4808   1.0000
   3.500   0.8048   0.00624   0.00172  -0.0895   0.4561   1.0000
   3.750   0.8310   0.00646   0.00185  -0.0892   0.4333   1.0000
   4.000   0.8571   0.00668   0.00200  -0.0890   0.4102   1.0000
   4.250   0.8830   0.00693   0.00217  -0.0887   0.3887   1.0000
   4.500   0.9090   0.00717   0.00233  -0.0884   0.3656   1.0000
   4.750   0.9341   0.00749   0.00253  -0.0881   0.3352   1.0000
   5.000   0.9580   0.00795   0.00278  -0.0875   0.2915   1.0000
   5.250   0.9822   0.00838   0.00303  -0.0871   0.2535   1.0000
   5.500   1.0064   0.00879   0.00331  -0.0866   0.2221   1.0000
   5.750   1.0299   0.00930   0.00363  -0.0860   0.1838   1.0000
   6.000   1.0531   0.00982   0.00397  -0.0854   0.1474   1.0000
   6.250   1.0747   0.01053   0.00441  -0.0846   0.1035   1.0000
   6.500   1.0967   0.01117   0.00487  -0.0838   0.0693   1.0000
   6.750   1.1164   0.01208   0.00553  -0.0827   0.0277   1.0000
   7.000   1.1369   0.01291   0.00621  -0.0816   0.0074   1.0000
   7.250   1.1602   0.01339   0.00673  -0.0809   0.0053   1.0000
   7.500   1.1834   0.01385   0.00726  -0.0801   0.0049   1.0000
   7.750   1.2057   0.01441   0.00789  -0.0792   0.0044   1.0000
   8.000   1.2273   0.01502   0.00857  -0.0783   0.0042   1.0000
   8.250   1.2482   0.01570   0.00935  -0.0772   0.0040   1.0000
   8.500   1.2678   0.01647   0.01022  -0.0759   0.0039   1.0000
   8.750   1.2864   0.01731   0.01116  -0.0745   0.0039   1.0000
   9.000   1.3039   0.01820   0.01215  -0.0729   0.0039   1.0000
   9.250   1.3202   0.01914   0.01320  -0.0712   0.0039   1.0000
   9.500   1.3344   0.02021   0.01438  -0.0692   0.0039   1.0000
   9.750   1.3471   0.02133   0.01561  -0.0670   0.0039   1.0000
  10.000   1.3564   0.02256   0.01695  -0.0643   0.0038   1.0000
  10.250   1.3621   0.02385   0.01834  -0.0611   0.0037   1.0000
  10.500   1.3652   0.02540   0.02003  -0.0577   0.0037   1.0000
  10.750   1.3713   0.02679   0.02153  -0.0549   0.0037   1.0000
  11.000   1.3769   0.02831   0.02318  -0.0522   0.0037   1.0000
  11.250   1.3816   0.02996   0.02496  -0.0497   0.0037   1.0000
  11.500   1.3844   0.03188   0.02702  -0.0472   0.0037   1.0000
  11.750   1.3882   0.03375   0.02905  -0.0450   0.0038   1.0000
  12.000   1.3886   0.03603   0.03148  -0.0428   0.0038   1.0000
  12.250   1.3884   0.03842   0.03403  -0.0409   0.0038   1.0000
  12.500   1.3861   0.04110   0.03689  -0.0391   0.0038   1.0000
  12.750   1.3763   0.04524   0.04133  -0.0372   0.0040   1.0000
  13.000   1.3691   0.04874   0.04501  -0.0362   0.0041   1.0000
  13.250   1.3615   0.05232   0.04875  -0.0358   0.0040   1.0000
  13.500   1.3216   0.06163   0.05856  -0.0361   0.0045   1.0000
  13.750   1.3020   0.06790   0.06505  -0.0378   0.0046   1.0000
  14.000   1.2794   0.07520   0.07257  -0.0406   0.0048   1.0000
  14.250   1.2567   0.08320   0.08076  -0.0445   0.0049   1.0000
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