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SG6042 (sg6042-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 100,000
Max Cl/Cd: 60.7 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6042-il-100000-n5.txt
Download as CSV file: xf-sg6042-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3771   0.10095   0.09624  -0.0331   1.0000   0.0477
  -8.000  -0.3872   0.09878   0.09416  -0.0317   1.0000   0.0476
  -7.750  -0.3973   0.09629   0.09174  -0.0316   0.9991   0.0473
  -7.500  -0.3966   0.08780   0.08322  -0.0389   0.9924   0.0301
  -7.250  -0.3842   0.08282   0.07823  -0.0447   0.9866   0.0293
  -7.000  -0.3710   0.07749   0.07289  -0.0514   0.9800   0.0292
  -6.750  -0.3542   0.07098   0.06630  -0.0601   0.9739   0.0291
  -6.500  -0.3418   0.06503   0.06025  -0.0660   0.9666   0.0291
  -6.250  -0.3226   0.05945   0.05450  -0.0718   0.9615   0.0288
  -6.000  -0.3070   0.05431   0.04917  -0.0756   0.9551   0.0283
  -5.750  -0.2858   0.04849   0.04303  -0.0800   0.9497   0.0278
  -5.500  -0.2578   0.04260   0.03665  -0.0847   0.9464   0.0275
  -5.250  -0.2393   0.03818   0.03173  -0.0858   0.9397   0.0275
  -5.000  -0.2101   0.03401   0.02690  -0.0880   0.9360   0.0283
  -4.750  -0.1769   0.03062   0.02275  -0.0901   0.9334   0.0301
  -4.500  -0.1521   0.02903   0.02095  -0.0903   0.9285   0.0313
  -4.250  -0.1238   0.02727   0.01885  -0.0908   0.9242   0.0323
  -4.000  -0.0912   0.02558   0.01682  -0.0918   0.9212   0.0338
  -3.750  -0.0565   0.02427   0.01510  -0.0930   0.9189   0.0367
  -3.500  -0.0317   0.02337   0.01421  -0.0928   0.9136   0.0394
  -3.250  -0.0030   0.02247   0.01321  -0.0930   0.9091   0.0423
  -3.000   0.0300   0.02154   0.01213  -0.0939   0.9060   0.0462
  -2.750   0.0651   0.02083   0.01142  -0.0954   0.9036   0.0549
  -2.500   0.0874   0.02030   0.01091  -0.0945   0.8968   0.0644
  -2.250   0.1188   0.01974   0.01036  -0.0952   0.8926   0.0845
  -2.000   0.1537   0.01914   0.00992  -0.0968   0.8898   0.1239
  -1.750   0.1811   0.01859   0.00962  -0.0969   0.8844   0.1808
  -1.500   0.2086   0.01772   0.00942  -0.0974   0.8791   0.3529
  -1.250   0.2365   0.01682   0.00949  -0.0970   0.8757   0.6419
  -1.000   0.2665   0.01646   0.00936  -0.0963   0.8730   0.7615
  -0.750   0.2796   0.01642   0.00943  -0.0927   0.8639   0.8311
  -0.500   0.3224   0.01607   0.00913  -0.0946   0.8610   0.9560
  -0.250   0.3657   0.01591   0.00878  -0.0976   0.8582   1.0000
   0.000   0.3872   0.01605   0.00878  -0.0966   0.8488   1.0000
   0.250   0.4246   0.01593   0.00853  -0.0983   0.8445   1.0000
   0.500   0.4510   0.01600   0.00849  -0.0980   0.8365   1.0000
   0.750   0.4848   0.01593   0.00832  -0.0990   0.8306   1.0000
   1.000   0.5157   0.01591   0.00822  -0.0994   0.8238   1.0000
   1.250   0.5458   0.01587   0.00812  -0.0997   0.8160   1.0000
   1.500   0.5765   0.01582   0.00801  -0.1000   0.8080   1.0000
   2.000   0.6351   0.01573   0.00785  -0.1000   0.7893   1.0000
   2.250   0.6716   0.01552   0.00760  -0.1013   0.7819   1.0000
   2.500   0.6960   0.01556   0.00764  -0.1004   0.7693   1.0000
   2.750   0.7226   0.01555   0.00762  -0.0998   0.7566   1.0000
   3.000   0.7503   0.01550   0.00758  -0.0995   0.7432   1.0000
   3.250   0.7783   0.01545   0.00753  -0.0991   0.7284   1.0000
   3.500   0.8063   0.01541   0.00747  -0.0988   0.7121   1.0000
   3.750   0.8351   0.01535   0.00742  -0.0985   0.6941   1.0000
   4.000   0.8627   0.01536   0.00740  -0.0981   0.6742   1.0000
   4.250   0.8885   0.01542   0.00744  -0.0973   0.6512   1.0000
   4.500   0.9147   0.01552   0.00747  -0.0967   0.6253   1.0000
   4.750   0.9402   0.01567   0.00756  -0.0959   0.5961   1.0000
   5.000   0.9640   0.01592   0.00769  -0.0948   0.5631   1.0000
   5.250   0.9863   0.01625   0.00788  -0.0935   0.5275   1.0000
   5.500   1.0071   0.01667   0.00817  -0.0921   0.4912   1.0000
   5.750   1.0262   0.01718   0.00852  -0.0904   0.4531   1.0000
   6.000   1.0440   0.01776   0.00892  -0.0886   0.4161   1.0000
   6.250   1.0607   0.01840   0.00940  -0.0867   0.3788   1.0000
   6.500   1.0766   0.01910   0.00995  -0.0847   0.3436   1.0000
   6.750   1.0917   0.01985   0.01054  -0.0826   0.3106   1.0000
   7.000   1.1067   0.02062   0.01118  -0.0806   0.2803   1.0000
   7.250   1.1215   0.02138   0.01184  -0.0786   0.2533   1.0000
   7.500   1.1356   0.02217   0.01256  -0.0766   0.2293   1.0000
   7.750   1.1494   0.02300   0.01331  -0.0745   0.2085   1.0000
   8.000   1.1631   0.02386   0.01411  -0.0725   0.1904   1.0000
   8.250   1.1773   0.02472   0.01494  -0.0706   0.1744   1.0000
   8.500   1.1909   0.02563   0.01585  -0.0686   0.1608   1.0000
   8.750   1.2040   0.02658   0.01679  -0.0667   0.1488   1.0000
   9.000   1.2181   0.02751   0.01777  -0.0649   0.1377   1.0000
   9.250   1.2313   0.02851   0.01882  -0.0631   0.1284   1.0000
   9.750   1.2561   0.03066   0.02107  -0.0595   0.1123   1.0000
  10.000   1.2666   0.03188   0.02229  -0.0576   0.1058   1.0000
  10.250   1.2795   0.03301   0.02356  -0.0559   0.0992   1.0000
  10.500   1.2883   0.03439   0.02491  -0.0540   0.0939   1.0000
  10.750   1.3011   0.03559   0.02631  -0.0525   0.0879   1.0000
  11.000   1.3103   0.03699   0.02777  -0.0508   0.0833   1.0000
  11.250   1.3202   0.03846   0.02936  -0.0492   0.0788   1.0000
  11.500   1.3299   0.03992   0.03097  -0.0477   0.0742   1.0000
  11.750   1.3368   0.04156   0.03266  -0.0461   0.0708   1.0000
  12.000   1.3455   0.04328   0.03453  -0.0447   0.0671   1.0000
  12.250   1.3532   0.04502   0.03646  -0.0433   0.0635   1.0000
  12.500   1.3588   0.04690   0.03845  -0.0420   0.0607   1.0000
  12.750   1.3635   0.04901   0.04059  -0.0407   0.0583   1.0000
  13.000   1.3691   0.05117   0.04304  -0.0395   0.0555   1.0000
  13.250   1.3728   0.05344   0.04551  -0.0385   0.0530   1.0000
  13.500   1.3749   0.05583   0.04802  -0.0375   0.0510   1.0000
  13.750   1.3765   0.05838   0.05064  -0.0367   0.0494   1.0000
  14.000   1.3773   0.06129   0.05374  -0.0360   0.0478   1.0000
  14.250   1.3753   0.06454   0.05729  -0.0355   0.0461   1.0000
  14.500   1.3716   0.06798   0.06101  -0.0353   0.0446   1.0000
  14.750   1.3669   0.07160   0.06482  -0.0354   0.0432   1.0000
  15.000   1.3618   0.07534   0.06874  -0.0357   0.0421   1.0000
  15.250   1.3568   0.07923   0.07277  -0.0363   0.0412   1.0000
  15.500   1.3522   0.08322   0.07687  -0.0371   0.0404   1.0000
  15.750   1.3465   0.08759   0.08135  -0.0381   0.0397   1.0000
  16.000   1.3308   0.09375   0.08782  -0.0404   0.0393   1.0000
  16.250   1.3130   0.10061   0.09497  -0.0435   0.0389   1.0000
  16.500   1.2923   0.10842   0.10306  -0.0476   0.0386   1.0000
  16.750   1.2681   0.11744   0.11233  -0.0529   0.0385   1.0000
  17.000   1.2391   0.12823   0.12336  -0.0598   0.0386   1.0000
  17.250   1.2015   0.14219   0.13753  -0.0692   0.0390   1.0000
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