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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 100,000
Max Cl/Cd: 59.62 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7075-il-100000.txt
Download as CSV file: xf-s7075-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7075 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3905   0.09407   0.08936  -0.0320   1.0000   0.0978
  -7.750  -0.4163   0.09319   0.08861  -0.0313   1.0000   0.0993
  -7.500  -0.4407   0.09176   0.08731  -0.0323   1.0000   0.0999
  -7.250  -0.4639   0.08910   0.08465  -0.0384   1.0000   0.1004
  -7.000  -0.4374   0.08512   0.08077  -0.0269   1.0000   0.1035
  -6.750  -0.4369   0.08279   0.07846  -0.0249   1.0000   0.1066
  -6.500  -0.4430   0.08006   0.07578  -0.0257   1.0000   0.1103
  -6.250  -0.4597   0.07528   0.07088  -0.0370   1.0000   0.1152
  -6.000  -0.4503   0.07291   0.06867  -0.0294   1.0000   0.1179
  -5.750  -0.4456   0.07052   0.06629  -0.0281   1.0000   0.1239
  -5.500  -0.4430   0.06603   0.06171  -0.0325   1.0000   0.1316
  -5.250  -0.4330   0.06337   0.05893  -0.0344   1.0000   0.1423
  -5.000  -0.4258   0.05989   0.05551  -0.0331   1.0000   0.1472
  -4.750  -0.4126   0.05638   0.05184  -0.0358   1.0000   0.1601
  -4.500  -0.4009   0.05397   0.04948  -0.0340   1.0000   0.1666
  -4.250  -0.3820   0.05069   0.04592  -0.0378   1.0000   0.1886
  -4.000  -0.3146   0.03408   0.02724  -0.0491   1.0000   0.0748
  -3.750  -0.2873   0.03098   0.02373  -0.0494   1.0000   0.0680
  -3.500  -0.2579   0.02778   0.01988  -0.0497   1.0000   0.0635
  -3.250  -0.2301   0.02564   0.01714  -0.0495   1.0000   0.0619
  -3.000  -0.2056   0.02428   0.01560  -0.0491   1.0000   0.0641
  -2.750  -0.1815   0.02328   0.01442  -0.0485   1.0000   0.0686
  -2.500  -0.1567   0.02228   0.01317  -0.0478   1.0000   0.0717
  -2.250  -0.1322   0.02101   0.01194  -0.0473   1.0000   0.0767
  -2.000  -0.1082   0.02022   0.01112  -0.0467   1.0000   0.0876
  -1.750  -0.0840   0.01936   0.01051  -0.0465   1.0000   0.1201
  -1.500  -0.0568   0.01738   0.01011  -0.0471   1.0000   0.3943
  -1.250  -0.0389   0.01642   0.01072  -0.0435   0.9963   0.8329
  -1.000   0.0127   0.01654   0.01061  -0.0485   0.9862   1.0000
  -0.750   0.0564   0.01707   0.01080  -0.0522   0.9769   1.0000
  -0.500   0.1018   0.01763   0.01107  -0.0561   0.9681   1.0000
  -0.250   0.1449   0.01807   0.01129  -0.0595   0.9582   1.0000
   0.000   0.1844   0.01843   0.01148  -0.0622   0.9471   1.0000
   0.250   0.2258   0.01878   0.01167  -0.0651   0.9367   1.0000
   0.500   0.2733   0.01909   0.01186  -0.0690   0.9280   1.0000
   0.750   0.3101   0.01927   0.01195  -0.0709   0.9157   1.0000
   1.000   0.3482   0.01941   0.01203  -0.0728   0.9038   1.0000
   1.250   0.3887   0.01949   0.01206  -0.0751   0.8926   1.0000
   1.500   0.4389   0.01938   0.01192  -0.0789   0.8844   1.0000
   1.750   0.4758   0.01928   0.01182  -0.0803   0.8716   1.0000
   2.000   0.5143   0.01911   0.01166  -0.0818   0.8593   1.0000
   2.250   0.5549   0.01882   0.01141  -0.0835   0.8475   1.0000
   2.500   0.5961   0.01838   0.01101  -0.0851   0.8364   1.0000
   2.750   0.6410   0.01772   0.01042  -0.0870   0.8268   1.0000
   3.000   0.6762   0.01722   0.00996  -0.0872   0.8127   1.0000
   3.250   0.7114   0.01667   0.00947  -0.0873   0.7978   1.0000
   3.500   0.7394   0.01634   0.00919  -0.0863   0.7780   1.0000
   3.750   0.7726   0.01585   0.00876  -0.0860   0.7590   1.0000
   4.000   0.8043   0.01545   0.00838  -0.0855   0.7370   1.0000
   4.250   0.8359   0.01515   0.00805  -0.0850   0.7120   1.0000
   4.500   0.8635   0.01509   0.00797  -0.0840   0.6821   1.0000
   4.750   0.8888   0.01520   0.00801  -0.0827   0.6488   1.0000
   5.000   0.9135   0.01540   0.00812  -0.0814   0.6139   1.0000
   5.250   0.9367   0.01571   0.00831  -0.0800   0.5772   1.0000
   5.500   0.9585   0.01610   0.00859  -0.0783   0.5385   1.0000
   5.750   0.9787   0.01656   0.00893  -0.0766   0.4975   1.0000
   6.000   0.9980   0.01710   0.00931  -0.0748   0.4555   1.0000
   6.250   1.0162   0.01772   0.00977  -0.0729   0.4124   1.0000
   6.500   1.0334   0.01843   0.01033  -0.0709   0.3686   1.0000
   6.750   1.0492   0.01926   0.01095  -0.0689   0.3236   1.0000
   7.000   1.0641   0.02022   0.01169  -0.0668   0.2789   1.0000
   7.250   1.0778   0.02134   0.01255  -0.0647   0.2352   1.0000
   7.500   1.0913   0.02263   0.01359  -0.0626   0.1955   1.0000
   7.750   1.1050   0.02407   0.01481  -0.0606   0.1642   1.0000
   8.000   1.1211   0.02561   0.01622  -0.0589   0.1404   1.0000
   8.250   1.1383   0.02712   0.01760  -0.0574   0.1233   1.0000
   8.500   1.1577   0.02867   0.01910  -0.0563   0.1103   1.0000
   8.750   1.1812   0.03053   0.02103  -0.0556   0.1014   1.0000
   9.000   1.2090   0.03286   0.02320  -0.0559   0.0942   1.0000
   9.250   1.2294   0.03446   0.02517  -0.0547   0.0889   1.0000
   9.500   1.2512   0.03622   0.02698  -0.0540   0.0838   1.0000
   9.750   1.2768   0.03929   0.03017  -0.0541   0.0807   1.0000
  10.000   1.2929   0.04173   0.03308  -0.0524   0.0788   1.0000
  10.250   1.3065   0.04456   0.03635  -0.0505   0.0772   1.0000
  10.500   1.3164   0.04747   0.03967  -0.0485   0.0756   1.0000
  10.750   1.3252   0.05017   0.04272  -0.0465   0.0736   1.0000
  11.000   1.3370   0.05278   0.04548  -0.0451   0.0715   1.0000
  11.250   1.3413   0.05628   0.04927  -0.0431   0.0706   1.0000
  11.500   1.3390   0.06016   0.05350  -0.0405   0.0703   1.0000
  11.750   1.3291   0.06401   0.05772  -0.0374   0.0703   1.0000
  12.000   1.3074   0.06754   0.06161  -0.0333   0.0708   1.0000
  12.250   1.2628   0.07191   0.06642  -0.0289   0.0720   1.0000
  12.500   1.2164   0.07793   0.07280  -0.0276   0.0733   1.0000
  12.750   1.1709   0.08553   0.08067  -0.0293   0.0747   1.0000
  13.000   1.1234   0.09538   0.09068  -0.0345   0.0764   1.0000
  13.250   1.0797   0.10749   0.10288  -0.0422   0.0786   1.0000
  13.500   1.0556   0.11795   0.11336  -0.0480   0.0803   1.0000
  13.750   1.0499   0.12523   0.12065  -0.0506   0.0812   1.0000
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