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SA7036 (sa7036-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 200,000
Max Cl/Cd: 69.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7036-il-200000-n5.txt
Download as CSV file: xf-sa7036-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7036                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3963   0.08238   0.07892  -0.0343   1.0000   0.0114
  -8.250  -0.3987   0.07910   0.07570  -0.0352   1.0000   0.0111
  -8.000  -0.4064   0.07530   0.07198  -0.0361   1.0000   0.0112
  -7.750  -0.4172   0.07256   0.06932  -0.0358   1.0000   0.0110
  -7.500  -0.4291   0.06923   0.06607  -0.0366   1.0000   0.0109
  -7.250  -0.4401   0.06525   0.06213  -0.0380   1.0000   0.0108
  -7.000  -0.4372   0.05920   0.05602  -0.0435   0.9972   0.0106
  -6.750  -0.4167   0.04929   0.04583  -0.0539   0.9894   0.0105
  -6.500  -0.3934   0.04022   0.03628  -0.0612   0.9833   0.0108
  -6.250  -0.3711   0.03347   0.02881  -0.0645   0.9761   0.0115
  -6.000  -0.3440   0.02837   0.02304  -0.0675   0.9715   0.0122
  -5.750  -0.3160   0.02510   0.01924  -0.0688   0.9668   0.0124
  -5.500  -0.2869   0.02263   0.01636  -0.0699   0.9618   0.0127
  -5.250  -0.2545   0.02065   0.01403  -0.0712   0.9582   0.0133
  -5.000  -0.2239   0.01907   0.01217  -0.0719   0.9537   0.0140
  -4.750  -0.1947   0.01776   0.01063  -0.0722   0.9478   0.0150
  -4.500  -0.1614   0.01694   0.00960  -0.0732   0.9437   0.0170
  -4.250  -0.1346   0.01562   0.00819  -0.0731   0.9370   0.0187
  -4.000  -0.1046   0.01477   0.00727  -0.0735   0.9311   0.0202
  -3.750  -0.0760   0.01410   0.00651  -0.0736   0.9245   0.0220
  -3.500  -0.0473   0.01357   0.00589  -0.0737   0.9174   0.0254
  -3.250  -0.0193   0.01298   0.00522  -0.0736   0.9101   0.0293
  -3.000   0.0092   0.01249   0.00465  -0.0735   0.9023   0.0371
  -2.750   0.0360   0.01196   0.00423  -0.0732   0.8932   0.0688
  -2.500   0.0636   0.01137   0.00390  -0.0732   0.8851   0.1418
  -2.250   0.0891   0.01078   0.00367  -0.0730   0.8747   0.2418
  -2.000   0.1144   0.01020   0.00352  -0.0726   0.8645   0.3635
  -1.750   0.1396   0.00969   0.00339  -0.0721   0.8545   0.4835
  -1.500   0.1648   0.00931   0.00328  -0.0712   0.8440   0.5812
  -1.250   0.1888   0.00901   0.00320  -0.0700   0.8318   0.6689
  -1.000   0.2122   0.00876   0.00313  -0.0685   0.8190   0.7445
  -0.750   0.2355   0.00857   0.00305  -0.0668   0.8056   0.8113
  -0.500   0.2618   0.00844   0.00295  -0.0657   0.7914   0.8780
  -0.250   0.2982   0.00835   0.00280  -0.0669   0.7765   0.9411
   0.000   0.3403   0.00830   0.00262  -0.0696   0.7603   0.9865
   0.250   0.3712   0.00834   0.00251  -0.0702   0.7427   1.0000
   0.500   0.3964   0.00842   0.00245  -0.0696   0.7247   1.0000
   0.750   0.4218   0.00852   0.00241  -0.0689   0.7065   1.0000
   1.000   0.4473   0.00863   0.00239  -0.0684   0.6880   1.0000
   1.250   0.4729   0.00876   0.00239  -0.0678   0.6685   1.0000
   1.500   0.4984   0.00891   0.00241  -0.0672   0.6490   1.0000
   1.750   0.5240   0.00906   0.00245  -0.0667   0.6291   1.0000
   2.000   0.5496   0.00923   0.00251  -0.0662   0.6090   1.0000
   2.250   0.5751   0.00941   0.00259  -0.0657   0.5895   1.0000
   2.500   0.6007   0.00960   0.00268  -0.0652   0.5690   1.0000
   3.000   0.6514   0.01003   0.00291  -0.0642   0.5266   1.0000
   3.250   0.6765   0.01027   0.00307  -0.0637   0.5052   1.0000
   3.500   0.7018   0.01050   0.00323  -0.0632   0.4843   1.0000
   3.750   0.7268   0.01076   0.00341  -0.0627   0.4640   1.0000
   4.000   0.7520   0.01102   0.00363  -0.0622   0.4437   1.0000
   4.250   0.7769   0.01130   0.00384  -0.0617   0.4232   1.0000
   4.500   0.8017   0.01159   0.00408  -0.0612   0.4031   1.0000
   4.750   0.8262   0.01190   0.00433  -0.0607   0.3819   1.0000
   5.000   0.8506   0.01224   0.00461  -0.0601   0.3601   1.0000
   5.250   0.8747   0.01259   0.00493  -0.0596   0.3385   1.0000
   5.500   0.8988   0.01295   0.00525  -0.0590   0.3181   1.0000
   5.750   0.9227   0.01332   0.00559  -0.0585   0.2982   1.0000
   6.000   0.9464   0.01373   0.00596  -0.0579   0.2794   1.0000
   6.250   0.9699   0.01414   0.00637  -0.0573   0.2593   1.0000
   6.500   0.9929   0.01460   0.00680  -0.0566   0.2396   1.0000
   6.750   1.0158   0.01506   0.00724  -0.0559   0.2193   1.0000
   7.000   1.0381   0.01558   0.00772  -0.0552   0.1994   1.0000
   7.250   1.0602   0.01611   0.00823  -0.0545   0.1802   1.0000
   7.500   1.0819   0.01667   0.00880  -0.0537   0.1614   1.0000
   7.750   1.1029   0.01729   0.00938  -0.0528   0.1439   1.0000
   8.000   1.1238   0.01791   0.01001  -0.0520   0.1267   1.0000
   8.250   1.1441   0.01858   0.01066  -0.0510   0.1096   1.0000
   8.500   1.1636   0.01931   0.01138  -0.0500   0.0941   1.0000
   8.750   1.1823   0.02009   0.01215  -0.0489   0.0804   1.0000
   9.000   1.2006   0.02088   0.01301  -0.0477   0.0690   1.0000
   9.250   1.2178   0.02173   0.01389  -0.0464   0.0585   1.0000
   9.500   1.2340   0.02264   0.01485  -0.0450   0.0498   1.0000
   9.750   1.2477   0.02370   0.01592  -0.0433   0.0428   1.0000
  10.000   1.2626   0.02461   0.01692  -0.0417   0.0363   1.0000
  10.250   1.2740   0.02562   0.01798  -0.0397   0.0299   1.0000
  10.500   1.2833   0.02674   0.01909  -0.0376   0.0242   1.0000
  10.750   1.2941   0.02775   0.02022  -0.0356   0.0200   1.0000
  11.000   1.3002   0.02913   0.02164  -0.0334   0.0165   1.0000
  11.250   1.3071   0.03046   0.02317  -0.0313   0.0144   1.0000
  11.500   1.3116   0.03205   0.02487  -0.0292   0.0121   1.0000
  11.750   1.3112   0.03409   0.02701  -0.0271   0.0108   1.0000
  12.000   1.3122   0.03613   0.02926  -0.0253   0.0093   1.0000
  12.250   1.3122   0.03836   0.03165  -0.0239   0.0085   1.0000
  12.500   1.3100   0.04094   0.03437  -0.0228   0.0079   1.0000
  12.750   1.3061   0.04385   0.03744  -0.0222   0.0076   1.0000
  13.000   1.2979   0.04747   0.04122  -0.0220   0.0073   1.0000
  13.250   1.2914   0.05115   0.04508  -0.0222   0.0070   1.0000
  13.500   1.2854   0.05502   0.04914  -0.0228   0.0067   1.0000
  13.750   1.2772   0.05941   0.05373  -0.0240   0.0065   1.0000
  14.000   1.2718   0.06365   0.05814  -0.0254   0.0062   1.0000
  14.250   1.2616   0.06881   0.06348  -0.0274   0.0061   1.0000
  14.500   1.2528   0.07403   0.06887  -0.0297   0.0058   1.0000
  14.750   1.2414   0.07993   0.07495  -0.0324   0.0058   1.0000
  15.000   1.2291   0.08622   0.08141  -0.0355   0.0058   1.0000
  15.250   1.2184   0.09255   0.08789  -0.0388   0.0055   1.0000
  15.500   1.2047   0.09957   0.09508  -0.0425   0.0055   1.0000
  15.750   1.1919   0.10670   0.10236  -0.0463   0.0055   1.0000
  16.000   1.1791   0.11408   0.10989  -0.0504   0.0054   1.0000
  16.250   1.1655   0.12178   0.11774  -0.0547   0.0054   1.0000
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