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SA7036 (sa7036-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 100,000
Max Cl/Cd: 53.92 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7036-il-100000.txt
Download as CSV file: xf-sa7036-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3817   0.09983   0.09496  -0.0275   1.0000   0.0887
  -8.500  -0.3925   0.09759   0.09282  -0.0312   1.0000   0.0918
  -8.250  -0.4125   0.09584   0.09123  -0.0354   1.0000   0.0926
  -8.000  -0.3893   0.09032   0.08569  -0.0315   1.0000   0.0955
  -7.750  -0.3821   0.08751   0.08292  -0.0303   1.0000   0.0989
  -7.500  -0.3877   0.08507   0.08057  -0.0303   1.0000   0.1022
  -7.250  -0.4086   0.08285   0.07850  -0.0328   1.0000   0.1053
  -7.000  -0.4368   0.08011   0.07573  -0.0413   1.0000   0.1067
  -6.750  -0.4183   0.07619   0.07198  -0.0332   1.0000   0.1094
  -6.500  -0.4154   0.07385   0.06969  -0.0307   1.0000   0.1128
  -6.000  -0.4289   0.06685   0.06265  -0.0353   1.0000   0.1226
  -5.750  -0.4229   0.06462   0.06050  -0.0318   1.0000   0.1263
  -5.500  -0.4238   0.06073   0.05643  -0.0356   1.0000   0.1364
  -5.250  -0.4163   0.05841   0.05422  -0.0323   1.0000   0.1407
  -5.000  -0.4101   0.05516   0.05086  -0.0334   1.0000   0.1523
  -4.750  -0.4016   0.05252   0.04818  -0.0330   1.0000   0.1664
  -4.500  -0.3918   0.05009   0.04569  -0.0321   1.0000   0.1813
  -4.250  -0.3406   0.03602   0.02964  -0.0414   1.0000   0.0780
  -4.000  -0.3144   0.03141   0.02430  -0.0412   1.0000   0.0646
  -3.750  -0.2908   0.02825   0.02078  -0.0410   1.0000   0.0617
  -3.500  -0.2651   0.02579   0.01785  -0.0406   1.0000   0.0598
  -3.250  -0.2397   0.02391   0.01556  -0.0400   1.0000   0.0599
  -3.000  -0.2162   0.02283   0.01417  -0.0392   1.0000   0.0640
  -2.750  -0.1925   0.02141   0.01259  -0.0385   1.0000   0.0677
  -2.500  -0.1699   0.02037   0.01156  -0.0378   1.0000   0.0727
  -2.250  -0.1276   0.01935   0.01054  -0.0406   0.9941   0.0899
  -2.000  -0.0870   0.01716   0.00934  -0.0433   0.9876   0.2367
  -1.750  -0.0591   0.01546   0.00981  -0.0427   0.9810   0.7301
  -1.500  -0.0040   0.01519   0.00964  -0.0468   0.9727   1.0000
  -1.250   0.0412   0.01549   0.00955  -0.0507   0.9619   1.0000
  -1.000   0.0865   0.01577   0.00952  -0.0545   0.9514   1.0000
  -0.750   0.1371   0.01602   0.00949  -0.0591   0.9427   1.0000
  -0.500   0.1778   0.01615   0.00943  -0.0618   0.9305   1.0000
  -0.250   0.2191   0.01625   0.00936  -0.0645   0.9186   1.0000
   0.000   0.2623   0.01628   0.00925  -0.0674   0.9073   1.0000
   0.250   0.3171   0.01614   0.00900  -0.0722   0.8999   1.0000
   0.500   0.3551   0.01605   0.00881  -0.0738   0.8871   1.0000
   0.750   0.3918   0.01592   0.00862  -0.0750   0.8742   1.0000
   1.000   0.4270   0.01576   0.00841  -0.0758   0.8612   1.0000
   1.250   0.4609   0.01558   0.00819  -0.0762   0.8478   1.0000
   1.500   0.4932   0.01537   0.00794  -0.0763   0.8339   1.0000
   1.750   0.5241   0.01517   0.00770  -0.0760   0.8193   1.0000
   2.000   0.5539   0.01497   0.00747  -0.0754   0.8041   1.0000
   2.250   0.5830   0.01478   0.00726  -0.0747   0.7883   1.0000
   2.500   0.6104   0.01467   0.00710  -0.0738   0.7707   1.0000
   2.750   0.6362   0.01464   0.00705  -0.0727   0.7510   1.0000
   3.000   0.6634   0.01459   0.00693  -0.0717   0.7322   1.0000
   3.250   0.6891   0.01464   0.00697  -0.0707   0.7112   1.0000
   3.500   0.7151   0.01471   0.00697  -0.0697   0.6898   1.0000
   3.750   0.7401   0.01485   0.00706  -0.0686   0.6668   1.0000
   4.000   0.7660   0.01500   0.00714  -0.0676   0.6448   1.0000
   4.250   0.7901   0.01524   0.00735  -0.0665   0.6200   1.0000
   4.500   0.8147   0.01550   0.00756  -0.0655   0.5959   1.0000
   4.750   0.8394   0.01579   0.00776  -0.0645   0.5722   1.0000
   5.000   0.8633   0.01612   0.00809  -0.0635   0.5471   1.0000
   5.250   0.8869   0.01649   0.00843  -0.0625   0.5216   1.0000
   5.500   0.9103   0.01689   0.00878  -0.0615   0.4961   1.0000
   5.750   0.9334   0.01731   0.00914  -0.0604   0.4705   1.0000
   6.000   0.9564   0.01778   0.00955  -0.0594   0.4452   1.0000
   6.250   0.9785   0.01828   0.01004  -0.0583   0.4187   1.0000
   6.500   1.0004   0.01882   0.01057  -0.0572   0.3927   1.0000
   6.750   1.0219   0.01942   0.01114  -0.0560   0.3670   1.0000
   7.000   1.0431   0.02006   0.01174  -0.0549   0.3418   1.0000
   7.250   1.0636   0.02074   0.01237  -0.0537   0.3167   1.0000
   7.500   1.0832   0.02145   0.01309  -0.0524   0.2910   1.0000
   7.750   1.1020   0.02221   0.01386  -0.0510   0.2653   1.0000
   8.000   1.1202   0.02306   0.01470  -0.0496   0.2407   1.0000
   8.250   1.1375   0.02400   0.01557  -0.0482   0.2169   1.0000
   8.500   1.1537   0.02500   0.01655  -0.0466   0.1932   1.0000
   8.750   1.1688   0.02614   0.01776  -0.0449   0.1701   1.0000
   9.000   1.1832   0.02748   0.01898  -0.0432   0.1493   1.0000
   9.250   1.1965   0.02887   0.02046  -0.0413   0.1294   1.0000
   9.500   1.2098   0.03043   0.02196  -0.0396   0.1130   1.0000
   9.750   1.2233   0.03216   0.02367  -0.0379   0.0991   1.0000
  10.000   1.2367   0.03401   0.02561  -0.0361   0.0873   1.0000
  10.250   1.2492   0.03607   0.02784  -0.0344   0.0774   1.0000
  10.500   1.2629   0.03857   0.03044  -0.0329   0.0690   1.0000
  11.000   1.2789   0.04322   0.03552  -0.0289   0.0557   1.0000
  11.500   1.2849   0.04882   0.04148  -0.0244   0.0471   1.0000
  11.750   1.2791   0.05146   0.04447  -0.0215   0.0446   1.0000
  12.000   1.2744   0.05378   0.04697  -0.0193   0.0417   1.0000
  12.250   1.2745   0.05706   0.05032  -0.0180   0.0396   1.0000
  12.500   1.2660   0.06228   0.05579  -0.0168   0.0386   1.0000
  12.750   1.2499   0.06676   0.06055  -0.0157   0.0384   1.0000
  13.000   1.2310   0.07109   0.06517  -0.0153   0.0383   1.0000
  13.250   1.2126   0.07600   0.07034  -0.0159   0.0383   1.0000
  13.500   1.1921   0.08152   0.07610  -0.0175   0.0383   1.0000
  13.750   1.1708   0.08773   0.08253  -0.0200   0.0384   1.0000
  14.000   1.1512   0.09375   0.08880  -0.0233   0.0387   1.0000
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