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SA7035 (sa7035-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 100,000
Max Cl/Cd: 53.33 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7035-il-100000-n5.txt
Download as CSV file: xf-sa7035-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4102   0.08661   0.08177  -0.0347   1.0000   0.0247
  -8.250  -0.4091   0.08341   0.07861  -0.0344   1.0000   0.0240
  -8.000  -0.4124   0.07959   0.07488  -0.0359   1.0000   0.0239
  -7.750  -0.4164   0.07650   0.07187  -0.0363   1.0000   0.0233
  -7.500  -0.4232   0.07267   0.06813  -0.0380   1.0000   0.0229
  -7.250  -0.4283   0.06831   0.06380  -0.0406   1.0000   0.0227
  -7.000  -0.4324   0.06437   0.05987  -0.0417   1.0000   0.0220
  -6.750  -0.4371   0.05996   0.05542  -0.0427   1.0000   0.0217
  -6.500  -0.4400   0.05567   0.05103  -0.0430   1.0000   0.0212
  -6.250  -0.4404   0.05134   0.04653  -0.0430   1.0000   0.0209
  -6.000  -0.4381   0.04677   0.04171  -0.0427   1.0000   0.0203
  -5.750  -0.4318   0.04232   0.03691  -0.0423   1.0000   0.0197
  -5.500  -0.4217   0.03795   0.03208  -0.0417   1.0000   0.0192
  -5.250  -0.3918   0.03303   0.02642  -0.0442   0.9953   0.0188
  -5.000  -0.3597   0.02948   0.02225  -0.0461   0.9901   0.0188
  -4.750  -0.3258   0.02672   0.01896  -0.0479   0.9853   0.0190
  -4.500  -0.2924   0.02453   0.01637  -0.0492   0.9804   0.0195
  -4.250  -0.2585   0.02269   0.01418  -0.0504   0.9750   0.0205
  -4.000  -0.2218   0.02117   0.01241  -0.0522   0.9707   0.0220
  -3.750  -0.1901   0.02002   0.01108  -0.0529   0.9637   0.0255
  -3.500  -0.1543   0.01889   0.00991  -0.0547   0.9585   0.0299
  -3.250  -0.1218   0.01787   0.00873  -0.0556   0.9515   0.0368
  -3.000  -0.0863   0.01681   0.00776  -0.0572   0.9456   0.0670
  -2.750  -0.0543   0.01556   0.00717  -0.0586   0.9390   0.1914
  -2.500  -0.0228   0.01458   0.00687  -0.0598   0.9319   0.3634
  -2.250   0.0066   0.01394   0.00669  -0.0601   0.9238   0.5050
  -2.000   0.0368   0.01346   0.00655  -0.0599   0.9163   0.6355
  -1.750   0.0619   0.01314   0.00645  -0.0584   0.9065   0.7374
  -1.500   0.0926   0.01287   0.00630  -0.0577   0.8991   0.8296
  -1.250   0.1329   0.01269   0.00608  -0.0592   0.8907   0.9120
  -1.000   0.1889   0.01249   0.00571  -0.0645   0.8848   0.9759
  -0.750   0.2293   0.01237   0.00541  -0.0670   0.8743   1.0000
  -0.500   0.2558   0.01233   0.00520  -0.0666   0.8611   1.0000
  -0.250   0.2823   0.01229   0.00502  -0.0662   0.8476   1.0000
   0.000   0.3090   0.01226   0.00486  -0.0657   0.8336   1.0000
   0.250   0.3356   0.01224   0.00471  -0.0653   0.8190   1.0000
   0.500   0.3623   0.01222   0.00459  -0.0647   0.8040   1.0000
   0.750   0.3891   0.01222   0.00448  -0.0642   0.7885   1.0000
   1.000   0.4152   0.01225   0.00441  -0.0636   0.7716   1.0000
   1.250   0.4413   0.01229   0.00437  -0.0630   0.7539   1.0000
   1.500   0.4676   0.01234   0.00432  -0.0624   0.7359   1.0000
   1.750   0.4940   0.01241   0.00429  -0.0618   0.7177   1.0000
   2.000   0.5196   0.01252   0.00432  -0.0611   0.6978   1.0000
   2.250   0.5455   0.01265   0.00437  -0.0604   0.6781   1.0000
   2.500   0.5712   0.01280   0.00444  -0.0598   0.6580   1.0000
   2.750   0.5967   0.01297   0.00453  -0.0592   0.6371   1.0000
   3.000   0.6222   0.01316   0.00465  -0.0585   0.6166   1.0000
   3.250   0.6474   0.01337   0.00483  -0.0579   0.5949   1.0000
   3.500   0.6725   0.01361   0.00499  -0.0572   0.5734   1.0000
   3.750   0.6973   0.01386   0.00519  -0.0565   0.5507   1.0000
   4.000   0.7220   0.01413   0.00541  -0.0558   0.5280   1.0000
   4.250   0.7465   0.01444   0.00568  -0.0551   0.5058   1.0000
   4.500   0.7710   0.01475   0.00597  -0.0545   0.4831   1.0000
   4.750   0.7952   0.01509   0.00627  -0.0538   0.4610   1.0000
   5.000   0.8192   0.01545   0.00661  -0.0531   0.4382   1.0000
   5.250   0.8429   0.01583   0.00701  -0.0524   0.4153   1.0000
   5.500   0.8662   0.01626   0.00739  -0.0516   0.3925   1.0000
   5.750   0.8895   0.01668   0.00783  -0.0509   0.3689   1.0000
   6.000   0.9124   0.01715   0.00829  -0.0501   0.3460   1.0000
   6.250   0.9349   0.01765   0.00881  -0.0493   0.3233   1.0000
   6.500   0.9573   0.01817   0.00936  -0.0485   0.3009   1.0000
   6.750   0.9789   0.01876   0.00993  -0.0476   0.2789   1.0000
   7.000   1.0004   0.01935   0.01055  -0.0468   0.2557   1.0000
   7.250   1.0212   0.02000   0.01121  -0.0458   0.2324   1.0000
   7.500   1.0410   0.02073   0.01191  -0.0448   0.2096   1.0000
   7.750   1.0610   0.02146   0.01272  -0.0439   0.1866   1.0000
   8.000   1.0800   0.02228   0.01355  -0.0428   0.1655   1.0000
   8.250   1.0981   0.02317   0.01445  -0.0417   0.1447   1.0000
   8.500   1.1155   0.02413   0.01544  -0.0404   0.1258   1.0000
   8.750   1.1319   0.02518   0.01652  -0.0391   0.1068   1.0000
   9.000   1.1463   0.02638   0.01771  -0.0376   0.0911   1.0000
   9.250   1.1592   0.02768   0.01905  -0.0360   0.0771   1.0000
   9.500   1.1706   0.02908   0.02047  -0.0343   0.0654   1.0000
   9.750   1.1816   0.03045   0.02197  -0.0324   0.0552   1.0000
  10.000   1.1898   0.03193   0.02357  -0.0303   0.0480   1.0000
  10.250   1.1922   0.03367   0.02530  -0.0277   0.0426   1.0000
  10.500   1.1984   0.03529   0.02715  -0.0255   0.0377   1.0000
  10.750   1.2006   0.03719   0.02918  -0.0233   0.0346   1.0000
  11.000   1.1988   0.03956   0.03161  -0.0212   0.0320   1.0000
  11.250   1.2025   0.04164   0.03395  -0.0197   0.0290   1.0000
  11.500   1.2034   0.04394   0.03641  -0.0184   0.0267   1.0000
  11.750   1.2017   0.04660   0.03920  -0.0173   0.0250   1.0000
  12.000   1.1979   0.04974   0.04244  -0.0165   0.0239   1.0000
  12.250   1.1963   0.05297   0.04586  -0.0159   0.0230   1.0000
  12.500   1.1938   0.05639   0.04963  -0.0156   0.0217   1.0000
  12.750   1.1891   0.06011   0.05361  -0.0160   0.0206   1.0000
  13.000   1.1825   0.06417   0.05788  -0.0169   0.0195   1.0000
  13.250   1.1753   0.06853   0.06244  -0.0181   0.0189   1.0000
  13.500   1.1665   0.07333   0.06742  -0.0200   0.0183   1.0000
  13.750   1.1564   0.07851   0.07277  -0.0223   0.0178   1.0000
  14.000   1.1450   0.08421   0.07864  -0.0250   0.0175   1.0000
  14.250   1.1325   0.09044   0.08505  -0.0282   0.0173   1.0000
  14.500   1.1186   0.09730   0.09211  -0.0319   0.0173   1.0000
  14.750   1.1029   0.10493   0.09993  -0.0363   0.0172   1.0000
  15.000   1.0844   0.11371   0.10892  -0.0417   0.0173   1.0000
  15.250   1.0584   0.12524   0.12069  -0.0489   0.0179   1.0000
  15.500   1.0110   0.14445   0.14008  -0.0603   0.0205   1.0000
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