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SA7036 (sa7036-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 50,000
Max Cl/Cd: 38.47 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7036-il-50000-n5.txt
Download as CSV file: xf-sa7036-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4115   0.08294   0.07643  -0.0403   1.0000   0.0461
  -7.500  -0.4116   0.07941   0.07297  -0.0409   1.0000   0.0457
  -7.250  -0.4125   0.07586   0.06949  -0.0413   1.0000   0.0452
  -7.000  -0.4140   0.07224   0.06591  -0.0419   1.0000   0.0446
  -6.750  -0.4155   0.06850   0.06218  -0.0425   1.0000   0.0439
  -6.500  -0.4164   0.06467   0.05833  -0.0431   1.0000   0.0432
  -6.250  -0.4157   0.06081   0.05439  -0.0436   1.0000   0.0425
  -6.000  -0.4132   0.05673   0.05017  -0.0441   1.0000   0.0419
  -5.750  -0.4077   0.05266   0.04587  -0.0445   1.0000   0.0413
  -5.500  -0.3991   0.04855   0.04146  -0.0448   1.0000   0.0409
  -5.250  -0.3870   0.04471   0.03724  -0.0449   1.0000   0.0407
  -5.000  -0.3719   0.04110   0.03319  -0.0449   1.0000   0.0408
  -4.750  -0.3543   0.03788   0.02949  -0.0446   1.0000   0.0415
  -4.500  -0.3343   0.03512   0.02617  -0.0442   1.0000   0.0440
  -4.250  -0.3124   0.03278   0.02317  -0.0435   1.0000   0.0462
  -4.000  -0.2914   0.03050   0.02060  -0.0430   1.0000   0.0481
  -3.750  -0.2695   0.02872   0.01858  -0.0421   1.0000   0.0501
  -3.500  -0.2471   0.02721   0.01682  -0.0412   1.0000   0.0529
  -3.250  -0.2246   0.02598   0.01529  -0.0401   1.0000   0.0573
  -3.000  -0.2028   0.02493   0.01419  -0.0393   1.0000   0.0650
  -2.750  -0.1735   0.02390   0.01296  -0.0396   0.9967   0.0751
  -2.500  -0.1352   0.02277   0.01180  -0.0420   0.9895   0.1047
  -2.250  -0.0965   0.02113   0.01099  -0.0451   0.9832   0.2434
  -2.000  -0.0669   0.01970   0.01089  -0.0458   0.9750   0.5235
  -1.750  -0.0436   0.01901   0.01099  -0.0431   0.9662   0.7693
  -1.500   0.0139   0.01876   0.01049  -0.0481   0.9583   1.0000
  -1.250   0.0521   0.01896   0.01025  -0.0506   0.9472   1.0000
  -1.000   0.0905   0.01916   0.01007  -0.0531   0.9362   1.0000
  -0.750   0.1303   0.01935   0.00992  -0.0557   0.9256   1.0000
  -0.500   0.1704   0.01951   0.00981  -0.0582   0.9148   1.0000
  -0.250   0.2061   0.01965   0.00973  -0.0599   0.9023   1.0000
   0.000   0.2418   0.01978   0.00965  -0.0615   0.8899   1.0000
   0.250   0.2764   0.01989   0.00961  -0.0628   0.8772   1.0000
   0.500   0.3102   0.01998   0.00957  -0.0638   0.8642   1.0000
   0.750   0.3432   0.02004   0.00951  -0.0646   0.8510   1.0000
   1.000   0.3755   0.02008   0.00947  -0.0652   0.8373   1.0000
   1.250   0.4071   0.02011   0.00943  -0.0656   0.8231   1.0000
   1.500   0.4381   0.02013   0.00940  -0.0658   0.8084   1.0000
   1.750   0.4685   0.02014   0.00937  -0.0658   0.7934   1.0000
   2.000   0.4987   0.02014   0.00934  -0.0657   0.7779   1.0000
   2.250   0.5287   0.02014   0.00931  -0.0655   0.7622   1.0000
   2.500   0.5586   0.02012   0.00929  -0.0653   0.7462   1.0000
   2.750   0.5855   0.02021   0.00937  -0.0646   0.7280   1.0000
   3.000   0.6129   0.02028   0.00944  -0.0640   0.7095   1.0000
   3.250   0.6412   0.02033   0.00948  -0.0634   0.6914   1.0000
   3.500   0.6678   0.02046   0.00964  -0.0627   0.6716   1.0000
   3.750   0.6940   0.02062   0.00980  -0.0618   0.6511   1.0000
   4.000   0.7205   0.02079   0.00996  -0.0610   0.6308   1.0000
   4.250   0.7455   0.02103   0.01027  -0.0601   0.6089   1.0000
   4.500   0.7708   0.02129   0.01053  -0.0592   0.5873   1.0000
   4.750   0.7954   0.02159   0.01084  -0.0582   0.5649   1.0000
   5.000   0.8193   0.02195   0.01122  -0.0572   0.5417   1.0000
   5.250   0.8436   0.02230   0.01156  -0.0562   0.5192   1.0000
   5.500   0.8664   0.02275   0.01211  -0.0552   0.4954   1.0000
   5.750   0.8892   0.02322   0.01262  -0.0541   0.4722   1.0000
   6.000   0.9121   0.02371   0.01312  -0.0530   0.4495   1.0000
   6.250   0.9337   0.02429   0.01378  -0.0519   0.4256   1.0000
   6.500   0.9552   0.02489   0.01447  -0.0508   0.4024   1.0000
   6.750   0.9762   0.02553   0.01513  -0.0496   0.3794   1.0000
   7.000   0.9960   0.02624   0.01593  -0.0483   0.3555   1.0000
   7.250   1.0155   0.02700   0.01673  -0.0470   0.3325   1.0000
   7.500   1.0342   0.02780   0.01759  -0.0457   0.3100   1.0000
   7.750   1.0522   0.02870   0.01857  -0.0443   0.2875   1.0000
   8.000   1.0695   0.02963   0.01958  -0.0429   0.2666   1.0000
   8.250   1.0853   0.03067   0.02075  -0.0414   0.2444   1.0000
   8.500   1.1002   0.03176   0.02184  -0.0398   0.2244   1.0000
   8.750   1.1134   0.03297   0.02319  -0.0382   0.2033   1.0000
   9.000   1.1255   0.03425   0.02450  -0.0364   0.1848   1.0000
   9.250   1.1362   0.03567   0.02601  -0.0346   0.1666   1.0000
   9.500   1.1459   0.03722   0.02766  -0.0328   0.1502   1.0000
  10.000   1.1600   0.04064   0.03133  -0.0288   0.1225   1.0000
  10.250   1.1645   0.04254   0.03331  -0.0267   0.1112   1.0000
  10.500   1.1672   0.04453   0.03535  -0.0248   0.1014   1.0000
  10.750   1.1718   0.04677   0.03774  -0.0231   0.0928   1.0000
  11.000   1.1746   0.04926   0.04045  -0.0216   0.0850   1.0000
  11.250   1.1746   0.05161   0.04278  -0.0203   0.0787   1.0000
  11.500   1.1754   0.05470   0.04623  -0.0191   0.0728   1.0000
  11.750   1.1762   0.05763   0.04930  -0.0182   0.0683   1.0000
  12.000   1.1746   0.06090   0.05269  -0.0176   0.0642   1.0000
  12.250   1.1663   0.06500   0.05716  -0.0175   0.0608   1.0000
  12.500   1.1581   0.06900   0.06137  -0.0180   0.0577   1.0000
  12.750   1.1557   0.07256   0.06496  -0.0183   0.0550   1.0000
  13.000   1.1470   0.07747   0.07006  -0.0193   0.0534   1.0000
  13.250   1.1301   0.08367   0.07658  -0.0217   0.0527   1.0000
  13.500   1.1112   0.09061   0.08379  -0.0250   0.0524   1.0000
  13.750   1.0904   0.09841   0.09181  -0.0292   0.0524   1.0000
  14.000   1.0690   0.10693   0.10051  -0.0342   0.0528   1.0000
  14.250   1.0467   0.11640   0.11011  -0.0399   0.0533   1.0000
  14.500   1.0244   0.12668   0.12047  -0.0461   0.0537   1.0000
  14.750   1.0030   0.13772   0.13151  -0.0526   0.0540   1.0000
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