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SA7035 (sa7035-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 500,000
Max Cl/Cd: 87.18 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7035-il-500000-n5.txt
Download as CSV file: xf-sa7035-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4084   0.08516   0.08292  -0.0297   1.0000   0.0069
  -8.250  -0.3549   0.05950   0.05748  -0.0360   1.0000   0.0049
  -8.000  -0.3675   0.05461   0.05264  -0.0373   1.0000   0.0049
  -7.750  -0.4478   0.06566   0.06362  -0.0374   0.9993   0.0049
  -7.500  -0.4321   0.05486   0.05273  -0.0533   0.9887   0.0047
  -7.250  -0.4155   0.04450   0.04209  -0.0639   0.9812   0.0046
  -7.000  -0.4002   0.03588   0.03306  -0.0692   0.9728   0.0044
  -6.750  -0.3878   0.02747   0.02398  -0.0712   0.9633   0.0042
  -6.500  -0.3686   0.02219   0.01802  -0.0716   0.9566   0.0041
  -6.250  -0.3487   0.01919   0.01449  -0.0708   0.9484   0.0042
  -6.000  -0.3249   0.01705   0.01195  -0.0703   0.9422   0.0044
  -5.750  -0.3015   0.01563   0.01024  -0.0695   0.9343   0.0045
  -5.500  -0.2765   0.01455   0.00894  -0.0689   0.9281   0.0048
  -5.250  -0.2517   0.01369   0.00791  -0.0683   0.9205   0.0049
  -5.000  -0.2272   0.01264   0.00670  -0.0676   0.9140   0.0052
  -4.750  -0.2024   0.01190   0.00586  -0.0670   0.9060   0.0056
  -4.500  -0.1766   0.01141   0.00528  -0.0666   0.8986   0.0060
  -4.250  -0.1505   0.01104   0.00485  -0.0662   0.8898   0.0067
  -4.000  -0.1243   0.01069   0.00442  -0.0658   0.8808   0.0075
  -3.750  -0.0981   0.01025   0.00388  -0.0653   0.8713   0.0078
  -3.500  -0.0716   0.00981   0.00335  -0.0649   0.8610   0.0083
  -3.250  -0.0449   0.00946   0.00289  -0.0645   0.8505   0.0095
  -3.000  -0.0179   0.00919   0.00254  -0.0642   0.8396   0.0122
  -2.750   0.0088   0.00885   0.00222  -0.0639   0.8277   0.0288
  -2.500   0.0353   0.00850   0.00200  -0.0637   0.8146   0.0709
  -2.250   0.0614   0.00804   0.00180  -0.0635   0.8005   0.1540
  -2.000   0.0876   0.00765   0.00165  -0.0633   0.7851   0.2411
  -1.750   0.1144   0.00745   0.00153  -0.0631   0.7686   0.2946
  -1.500   0.1410   0.00724   0.00142  -0.0629   0.7515   0.3582
  -1.250   0.1675   0.00706   0.00134  -0.0627   0.7341   0.4237
  -1.000   0.1938   0.00686   0.00130  -0.0624   0.7171   0.5007
  -0.750   0.2200   0.00668   0.00128  -0.0621   0.6996   0.5796
  -0.500   0.2462   0.00657   0.00126  -0.0617   0.6814   0.6397
  -0.250   0.2723   0.00652   0.00126  -0.0612   0.6625   0.6884
   0.000   0.2982   0.00648   0.00127  -0.0607   0.6430   0.7346
   0.250   0.3237   0.00644   0.00130  -0.0601   0.6239   0.7814
   0.500   0.3482   0.00641   0.00133  -0.0591   0.6054   0.8296
   0.750   0.3716   0.00640   0.00137  -0.0579   0.5878   0.8800
   1.000   0.3970   0.00643   0.00140  -0.0570   0.5698   0.9297
   1.250   0.4307   0.00652   0.00142  -0.0582   0.5499   0.9662
   1.500   0.4675   0.00664   0.00144  -0.0602   0.5292   0.9927
   1.750   0.4965   0.00679   0.00148  -0.0605   0.5081   1.0000
   2.000   0.5223   0.00697   0.00155  -0.0602   0.4871   1.0000
   2.250   0.5483   0.00714   0.00163  -0.0598   0.4665   1.0000
   2.500   0.5744   0.00732   0.00172  -0.0595   0.4480   1.0000
   2.750   0.6008   0.00749   0.00181  -0.0593   0.4300   1.0000
   3.000   0.6270   0.00768   0.00192  -0.0590   0.4112   1.0000
   3.250   0.6531   0.00789   0.00206  -0.0588   0.3927   1.0000
   3.500   0.6794   0.00809   0.00219  -0.0585   0.3739   1.0000
   3.750   0.7054   0.00832   0.00234  -0.0583   0.3534   1.0000
   4.000   0.7313   0.00857   0.00251  -0.0580   0.3327   1.0000
   4.250   0.7574   0.00881   0.00269  -0.0578   0.3139   1.0000
   4.500   0.7831   0.00907   0.00288  -0.0575   0.2949   1.0000
   4.750   0.8090   0.00933   0.00308  -0.0572   0.2777   1.0000
   5.000   0.8349   0.00958   0.00331  -0.0570   0.2615   1.0000
   5.250   0.8605   0.00987   0.00354  -0.0567   0.2427   1.0000
   5.500   0.8856   0.01021   0.00380  -0.0564   0.2228   1.0000
   5.750   0.9106   0.01056   0.00408  -0.0560   0.2009   1.0000
   6.000   0.9353   0.01095   0.00438  -0.0556   0.1804   1.0000
   6.250   0.9601   0.01131   0.00470  -0.0553   0.1626   1.0000
   6.500   0.9847   0.01168   0.00504  -0.0549   0.1466   1.0000
   6.750   1.0088   0.01211   0.00540  -0.0544   0.1295   1.0000
   7.000   1.0330   0.01252   0.00578  -0.0540   0.1152   1.0000
   7.250   1.0569   0.01297   0.00620  -0.0535   0.0997   1.0000
   7.500   1.0796   0.01353   0.00667  -0.0529   0.0805   1.0000
   7.750   1.1020   0.01410   0.00717  -0.0523   0.0645   1.0000
   8.000   1.1245   0.01464   0.00768  -0.0516   0.0524   1.0000
   8.250   1.1466   0.01522   0.00823  -0.0509   0.0417   1.0000
   8.500   1.1684   0.01580   0.00880  -0.0502   0.0338   1.0000
   8.750   1.1905   0.01633   0.00939  -0.0495   0.0285   1.0000
   9.000   1.2114   0.01697   0.01004  -0.0486   0.0233   1.0000
   9.250   1.2324   0.01755   0.01067  -0.0478   0.0193   1.0000
   9.500   1.2521   0.01825   0.01140  -0.0467   0.0153   1.0000
   9.750   1.2711   0.01898   0.01215  -0.0457   0.0122   1.0000
  10.000   1.2897   0.01970   0.01293  -0.0445   0.0101   1.0000
  10.250   1.3076   0.02044   0.01374  -0.0433   0.0087   1.0000
  10.500   1.3230   0.02136   0.01472  -0.0418   0.0074   1.0000
  10.750   1.3395   0.02208   0.01555  -0.0404   0.0065   1.0000
  11.000   1.3537   0.02287   0.01642  -0.0387   0.0056   1.0000
  11.250   1.3637   0.02380   0.01743  -0.0364   0.0050   1.0000
  11.500   1.3717   0.02486   0.01859  -0.0339   0.0045   1.0000
  11.750   1.3810   0.02584   0.01969  -0.0318   0.0040   1.0000
  12.000   1.3885   0.02699   0.02096  -0.0297   0.0038   1.0000
  12.250   1.3955   0.02821   0.02228  -0.0277   0.0035   1.0000
  12.500   1.4004   0.02965   0.02383  -0.0258   0.0031   1.0000
  12.750   1.4018   0.03146   0.02575  -0.0238   0.0029   1.0000
  13.000   1.4022   0.03347   0.02790  -0.0222   0.0027   1.0000
  13.250   1.4044   0.03543   0.03000  -0.0210   0.0026   1.0000
  13.500   1.4046   0.03772   0.03246  -0.0200   0.0024   1.0000
  13.750   1.4013   0.04054   0.03543  -0.0194   0.0024   1.0000
  14.000   1.3989   0.04349   0.03853  -0.0193   0.0022   1.0000
  14.250   1.3961   0.04668   0.04186  -0.0195   0.0020   1.0000
  14.500   1.3894   0.05058   0.04592  -0.0203   0.0020   1.0000
  14.750   1.3832   0.05467   0.05015  -0.0215   0.0019   1.0000
  15.000   1.3718   0.05980   0.05545  -0.0233   0.0020   1.0000
  15.250   1.3611   0.06513   0.06093  -0.0256   0.0019   1.0000
  15.500   1.3511   0.07059   0.06653  -0.0281   0.0018   1.0000
  15.750   1.3359   0.07725   0.07336  -0.0314   0.0019   1.0000
  16.000   1.3218   0.08395   0.08020  -0.0348   0.0018   1.0000
  16.250   1.3021   0.09200   0.08843  -0.0390   0.0019   1.0000
  16.500   1.2852   0.09978   0.09636  -0.0432   0.0018   1.0000
  16.750   1.2665   0.10816   0.10488  -0.0477   0.0018   1.0000
  17.000   1.2476   0.11684   0.11370  -0.0524   0.0019   1.0000
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