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SA7035 (sa7035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.22 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7035-il-1000000-n5.txt
Download as CSV file: xf-sa7035-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4559   0.02814   0.02560  -0.0704   0.9488   0.0026
  -7.250  -0.4530   0.02112   0.01779  -0.0692   0.9372   0.0025
  -7.000  -0.4360   0.01825   0.01447  -0.0681   0.9292   0.0025
  -6.750  -0.4152   0.01615   0.01201  -0.0673   0.9211   0.0026
  -6.500  -0.3926   0.01473   0.01031  -0.0666   0.9139   0.0026
  -6.250  -0.3682   0.01364   0.00901  -0.0661   0.9066   0.0027
  -6.000  -0.3433   0.01282   0.00800  -0.0656   0.9000   0.0027
  -5.750  -0.3175   0.01215   0.00719  -0.0653   0.8925   0.0028
  -5.500  -0.2938   0.01080   0.00561  -0.0646   0.8848   0.0031
  -5.250  -0.2676   0.01030   0.00501  -0.0643   0.8760   0.0033
  -5.000  -0.2409   0.00993   0.00457  -0.0640   0.8670   0.0035
  -4.750  -0.2143   0.00959   0.00415  -0.0638   0.8567   0.0038
  -4.500  -0.1875   0.00926   0.00373  -0.0635   0.8455   0.0040
  -4.250  -0.1605   0.00894   0.00332  -0.0633   0.8342   0.0043
  -4.000  -0.1333   0.00868   0.00298  -0.0631   0.8227   0.0045
  -3.750  -0.1061   0.00845   0.00267  -0.0629   0.8101   0.0047
  -3.500  -0.0788   0.00827   0.00242  -0.0627   0.7965   0.0051
  -3.250  -0.0516   0.00802   0.00206  -0.0625   0.7817   0.0059
  -3.000  -0.0242   0.00787   0.00182  -0.0623   0.7652   0.0068
  -2.750   0.0032   0.00775   0.00161  -0.0622   0.7479   0.0085
  -2.500   0.0304   0.00758   0.00142  -0.0620   0.7304   0.0201
  -2.250   0.0577   0.00740   0.00127  -0.0619   0.7129   0.0465
  -1.750   0.1116   0.00686   0.00104  -0.0618   0.6787   0.1713
  -1.500   0.1387   0.00668   0.00097  -0.0618   0.6615   0.2300
  -1.250   0.1662   0.00659   0.00091  -0.0617   0.6435   0.2685
  -1.000   0.1934   0.00647   0.00087  -0.0617   0.6238   0.3210
  -0.750   0.2205   0.00638   0.00084  -0.0616   0.6041   0.3755
  -0.500   0.2477   0.00626   0.00083  -0.0616   0.5857   0.4396
  -0.250   0.2748   0.00612   0.00083  -0.0616   0.5683   0.5099
   0.000   0.3020   0.00606   0.00084  -0.0615   0.5507   0.5659
   0.250   0.3293   0.00603   0.00087  -0.0614   0.5333   0.6119
   0.500   0.3565   0.00601   0.00090  -0.0613   0.5159   0.6542
   0.750   0.3836   0.00600   0.00094  -0.0612   0.4989   0.6960
   1.000   0.4105   0.00601   0.00099  -0.0610   0.4802   0.7371
   1.250   0.4369   0.00603   0.00106  -0.0607   0.4601   0.7794
   1.500   0.4628   0.00605   0.00112  -0.0602   0.4389   0.8233
   1.750   0.4877   0.00606   0.00120  -0.0595   0.4214   0.8700
   2.000   0.5108   0.00607   0.00128  -0.0583   0.4067   0.9200
   2.250   0.5383   0.00615   0.00135  -0.0580   0.3898   0.9639
   2.500   0.5735   0.00627   0.00141  -0.0597   0.3722   0.9907
   2.750   0.6034   0.00643   0.00149  -0.0603   0.3545   1.0000
   3.250   0.6566   0.00682   0.00171  -0.0599   0.3159   1.0000
   3.500   0.6831   0.00702   0.00182  -0.0597   0.2973   1.0000
   3.750   0.7097   0.00723   0.00195  -0.0596   0.2801   1.0000
   4.000   0.7363   0.00743   0.00210  -0.0594   0.2637   1.0000
   4.250   0.7629   0.00762   0.00224  -0.0593   0.2501   1.0000
   4.500   0.7895   0.00783   0.00239  -0.0591   0.2356   1.0000
   4.750   0.8158   0.00806   0.00257  -0.0589   0.2190   1.0000
   5.000   0.8419   0.00832   0.00276  -0.0587   0.2013   1.0000
   5.250   0.8675   0.00864   0.00298  -0.0585   0.1795   1.0000
   5.500   0.8932   0.00895   0.00321  -0.0582   0.1606   1.0000
   5.750   0.9190   0.00923   0.00343  -0.0580   0.1463   1.0000
   6.000   0.9445   0.00954   0.00369  -0.0577   0.1313   1.0000
   6.250   0.9699   0.00987   0.00396  -0.0574   0.1164   1.0000
   6.500   0.9952   0.01019   0.00424  -0.0571   0.1036   1.0000
   6.750   1.0199   0.01058   0.00455  -0.0568   0.0877   1.0000
   7.000   1.0442   0.01100   0.00490  -0.0563   0.0712   1.0000
   7.250   1.0683   0.01145   0.00529  -0.0559   0.0569   1.0000
   7.500   1.0921   0.01191   0.00568  -0.0554   0.0446   1.0000
   7.750   1.1164   0.01231   0.00606  -0.0550   0.0371   1.0000
   8.000   1.1404   0.01271   0.00646  -0.0545   0.0310   1.0000
   8.250   1.1641   0.01315   0.00688  -0.0540   0.0256   1.0000
   8.500   1.1878   0.01356   0.00731  -0.0535   0.0216   1.0000
   8.750   1.2103   0.01409   0.00782  -0.0528   0.0157   1.0000
   9.250   1.2545   0.01516   0.00888  -0.0515   0.0087   1.0000
   9.500   1.2764   0.01569   0.00943  -0.0507   0.0069   1.0000
   9.750   1.2983   0.01619   0.00997  -0.0500   0.0061   1.0000
  10.000   1.3192   0.01674   0.01056  -0.0491   0.0052   1.0000
  10.250   1.3397   0.01732   0.01119  -0.0482   0.0045   1.0000
  10.500   1.3603   0.01786   0.01180  -0.0473   0.0041   1.0000
  10.750   1.3798   0.01844   0.01244  -0.0463   0.0035   1.0000
  11.000   1.3980   0.01911   0.01316  -0.0451   0.0030   1.0000
  11.250   1.4154   0.01980   0.01391  -0.0438   0.0027   1.0000
  11.500   1.4325   0.02045   0.01463  -0.0425   0.0023   1.0000
  11.750   1.4470   0.02119   0.01543  -0.0408   0.0019   1.0000
  12.000   1.4584   0.02194   0.01625  -0.0386   0.0018   1.0000
  12.250   1.4668   0.02285   0.01724  -0.0360   0.0015   1.0000
  12.500   1.4758   0.02374   0.01822  -0.0337   0.0014   1.0000
  12.750   1.4839   0.02474   0.01932  -0.0315   0.0013   1.0000
  13.000   1.4909   0.02585   0.02053  -0.0293   0.0012   1.0000
  13.250   1.4977   0.02703   0.02180  -0.0274   0.0011   1.0000
  13.500   1.5021   0.02845   0.02331  -0.0254   0.0010   1.0000
  13.750   1.5065   0.02995   0.02492  -0.0237   0.0010   1.0000
  14.000   1.5077   0.03182   0.02690  -0.0221   0.0009   1.0000
  14.250   1.5064   0.03403   0.02922  -0.0206   0.0008   1.0000
  14.500   1.5079   0.03614   0.03145  -0.0197   0.0008   1.0000
  14.750   1.5019   0.03917   0.03462  -0.0190   0.0008   1.0000
  15.000   1.5027   0.04169   0.03725  -0.0188   0.0008   1.0000
  15.250   1.4935   0.04557   0.04128  -0.0191   0.0007   1.0000
  15.500   1.4748   0.05105   0.04695  -0.0202   0.0007   1.0000
  15.750   1.4735   0.05448   0.05049  -0.0213   0.0007   1.0000
  16.000   1.4525   0.06108   0.05728  -0.0238   0.0007   1.0000
  16.250   1.4474   0.06556   0.06186  -0.0258   0.0007   1.0000
  16.500   1.4289   0.07253   0.06900  -0.0291   0.0007   1.0000
  16.750   1.4079   0.08033   0.07696  -0.0331   0.0007   1.0000
  17.000   1.3898   0.08789   0.08466  -0.0370   0.0007   1.0000
  17.250   1.3626   0.09762   0.09457  -0.0423   0.0007   1.0000
  17.500   1.3517   0.10422   0.10127  -0.0458   0.0007   1.0000
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