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SA7025 (sa7025-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7025 (sa7025-il)
Reynolds number: 200,000
Max Cl/Cd: 83.27 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7025-il-200000.txt
Download as CSV file: xf-sa7025-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3654   0.08796   0.08479  -0.0287   1.0000   0.0345
  -7.250  -0.3774   0.08661   0.08351  -0.0258   1.0000   0.0349
  -7.000  -0.3919   0.08529   0.08226  -0.0229   1.0000   0.0352
  -6.750  -0.3999   0.08333   0.08036  -0.0217   1.0000   0.0357
  -6.500  -0.4061   0.08110   0.07818  -0.0210   1.0000   0.0366
  -6.250  -0.4102   0.07858   0.07569  -0.0212   1.0000   0.0373
  -6.000  -0.4117   0.07580   0.07293  -0.0221   1.0000   0.0381
  -5.750  -0.3978   0.07144   0.06855  -0.0283   0.9984   0.0413
  -5.500  -0.3419   0.06106   0.05778  -0.0507   0.9919   0.0443
  -5.250  -0.3304   0.05846   0.05536  -0.0484   0.9883   0.0468
  -5.000  -0.2973   0.05434   0.05114  -0.0540   0.9844   0.0500
  -4.750  -0.2472   0.04692   0.04296  -0.0668   0.9778   0.0574
  -4.500  -0.2223   0.04297   0.03918  -0.0687   0.9741   0.0596
  -4.250  -0.1853   0.03983   0.03588  -0.0729   0.9709   0.0650
  -4.000  -0.1523   0.03573   0.03137  -0.0766   0.9648   0.0732
  -3.750  -0.1141   0.03286   0.02806  -0.0803   0.9603   0.0856
  -3.500  -0.0764   0.03028   0.02546  -0.0833   0.9576   0.0919
  -3.250  -0.0265   0.02157   0.01502  -0.0840   0.9561   0.0338
  -3.000   0.0047   0.02054   0.01364  -0.0840   0.9491   0.0321
  -2.750   0.0431   0.01826   0.01111  -0.0861   0.9461   0.0345
  -2.500   0.0850   0.01695   0.00965  -0.0886   0.9436   0.0358
  -2.250   0.1148   0.01598   0.00862  -0.0886   0.9365   0.0365
  -2.000   0.1549   0.01509   0.00768  -0.0908   0.9326   0.0390
  -1.750   0.1993   0.01423   0.00674  -0.0938   0.9300   0.0490
  -1.500   0.2270   0.01265   0.00633  -0.0943   0.9225   0.3470
  -1.250   0.2540   0.01122   0.00632  -0.0938   0.9178   0.7297
  -1.000   0.3098   0.01061   0.00592  -0.0984   0.9166   1.0000
  -0.750   0.3385   0.01056   0.00569  -0.0983   0.9075   1.0000
  -0.500   0.3752   0.01037   0.00535  -0.0996   0.9024   1.0000
  -0.250   0.4022   0.01030   0.00516  -0.0991   0.8924   1.0000
   0.000   0.4330   0.01014   0.00490  -0.0992   0.8848   1.0000
   0.250   0.4617   0.01000   0.00466  -0.0988   0.8759   1.0000
   0.500   0.4882   0.00991   0.00449  -0.0981   0.8653   1.0000
   0.750   0.5157   0.00979   0.00430  -0.0976   0.8553   1.0000
   1.000   0.5442   0.00964   0.00407  -0.0971   0.8459   1.0000
   1.250   0.5704   0.00955   0.00393  -0.0963   0.8335   1.0000
   1.500   0.5966   0.00948   0.00380  -0.0956   0.8202   1.0000
   1.750   0.6231   0.00942   0.00368  -0.0948   0.8061   1.0000
   2.000   0.6495   0.00938   0.00358  -0.0941   0.7909   1.0000
   2.250   0.6753   0.00938   0.00357  -0.0934   0.7732   1.0000
   2.500   0.7015   0.00941   0.00353  -0.0927   0.7552   1.0000
   2.750   0.7279   0.00946   0.00350  -0.0920   0.7368   1.0000
   3.000   0.7536   0.00956   0.00355  -0.0913   0.7157   1.0000
   3.250   0.7795   0.00969   0.00361  -0.0906   0.6947   1.0000
   3.500   0.8047   0.00986   0.00372  -0.0899   0.6711   1.0000
   3.750   0.8298   0.01007   0.00385  -0.0892   0.6475   1.0000
   4.000   0.8547   0.01031   0.00401  -0.0884   0.6236   1.0000
   4.250   0.8792   0.01057   0.00419  -0.0876   0.5987   1.0000
   4.500   0.9035   0.01085   0.00445  -0.0868   0.5727   1.0000
   4.750   0.9273   0.01115   0.00469  -0.0860   0.5458   1.0000
   5.000   0.9509   0.01148   0.00496  -0.0851   0.5184   1.0000
   5.250   0.9743   0.01184   0.00526  -0.0843   0.4911   1.0000
   5.500   0.9973   0.01223   0.00562  -0.0834   0.4635   1.0000
   5.750   1.0200   0.01264   0.00598  -0.0824   0.4352   1.0000
   6.000   1.0422   0.01308   0.00637  -0.0815   0.4060   1.0000
   6.250   1.0637   0.01358   0.00679  -0.0804   0.3752   1.0000
   6.500   1.0850   0.01409   0.00725  -0.0793   0.3431   1.0000
   6.750   1.1052   0.01466   0.00776  -0.0782   0.3079   1.0000
   7.000   1.1236   0.01537   0.00827  -0.0768   0.2626   1.0000
   7.250   1.1419   0.01613   0.00885  -0.0755   0.2168   1.0000
   7.500   1.1606   0.01693   0.00953  -0.0743   0.1809   1.0000
   7.750   1.1777   0.01790   0.01028  -0.0729   0.1358   1.0000
   8.000   1.1922   0.01917   0.01127  -0.0713   0.0860   1.0000
   8.250   1.1939   0.02195   0.01356  -0.0675   0.0290   1.0000
   8.500   1.2025   0.02372   0.01541  -0.0647   0.0224   1.0000
   8.750   1.2159   0.02493   0.01680  -0.0626   0.0195   1.0000
   9.000   1.2259   0.02633   0.01833  -0.0600   0.0179   1.0000
   9.250   1.2333   0.02783   0.01994  -0.0572   0.0170   1.0000
   9.500   1.2394   0.02959   0.02179  -0.0543   0.0161   1.0000
   9.750   1.2463   0.03167   0.02398  -0.0518   0.0155   1.0000
  10.000   1.2567   0.03439   0.02683  -0.0498   0.0150   1.0000
  10.250   1.2726   0.03751   0.03014  -0.0485   0.0148   1.0000
  10.500   1.2878   0.04086   0.03376  -0.0473   0.0147   1.0000
  10.750   1.2976   0.04363   0.03680  -0.0455   0.0148   1.0000
  11.000   1.3027   0.04640   0.03984  -0.0433   0.0149   1.0000
  11.250   1.3049   0.04884   0.04254  -0.0409   0.0150   1.0000
  11.500   1.3031   0.05151   0.04549  -0.0385   0.0153   1.0000
  11.750   1.2973   0.05449   0.04883  -0.0362   0.0155   1.0000
  12.000   1.2857   0.05826   0.05297  -0.0341   0.0160   1.0000
  12.250   1.2697   0.06302   0.05811  -0.0327   0.0166   1.0000
  12.500   1.2463   0.06849   0.06395  -0.0324   0.0171   1.0000
  12.750   1.2237   0.07438   0.07008  -0.0334   0.0174   1.0000
  13.000   1.2015   0.08070   0.07666  -0.0355   0.0177   1.0000
  13.250   1.1794   0.08767   0.08386  -0.0388   0.0180   1.0000
  13.500   1.1573   0.09531   0.09169  -0.0432   0.0181   1.0000
  13.750   1.1355   0.10370   0.10026  -0.0486   0.0182   1.0000
  14.000   1.1131   0.11325   0.10997  -0.0552   0.0183   1.0000
  14.250   1.0898   0.12418   0.12103  -0.0628   0.0184   1.0000
  14.500   1.0637   0.13753   0.13448  -0.0717   0.0187   1.0000
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