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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 100,000
Max Cl/Cd: 60.75 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4061-il-100000-n5.txt
Download as CSV file: xf-s4061-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3294   0.09012   0.08541  -0.0396   1.0000   0.0301
  -8.250  -0.3263   0.08732   0.08267  -0.0399   1.0000   0.0294
  -8.000  -0.3283   0.08455   0.08000  -0.0400   1.0000   0.0287
  -7.750  -0.3398   0.08246   0.07804  -0.0386   1.0000   0.0282
  -7.500  -0.3423   0.07933   0.07498  -0.0405   0.9913   0.0275
  -7.250  -0.3283   0.06603   0.06163  -0.0599   0.9744   0.0244
  -7.000  -0.3075   0.05993   0.05546  -0.0683   0.9640   0.0241
  -6.750  -0.2866   0.05240   0.04774  -0.0774   0.9537   0.0237
  -6.500  -0.2656   0.04467   0.03963  -0.0857   0.9441   0.0233
  -6.250  -0.2471   0.03838   0.03279  -0.0905   0.9333   0.0230
  -6.000  -0.2261   0.03345   0.02720  -0.0931   0.9241   0.0230
  -5.750  -0.2008   0.02958   0.02264  -0.0947   0.9170   0.0233
  -5.500  -0.1769   0.02689   0.01937  -0.0949   0.9085   0.0238
  -5.250  -0.1494   0.02498   0.01708  -0.0954   0.9022   0.0252
  -5.000  -0.1241   0.02390   0.01582  -0.0954   0.8943   0.0275
  -4.750  -0.0965   0.02245   0.01404  -0.0953   0.8880   0.0294
  -4.500  -0.0706   0.02116   0.01250  -0.0949   0.8806   0.0310
  -4.250  -0.0443   0.02013   0.01138  -0.0946   0.8738   0.0336
  -4.000  -0.0180   0.01930   0.01037  -0.0942   0.8670   0.0384
  -3.750   0.0081   0.01854   0.00956  -0.0939   0.8598   0.0480
  -3.500   0.0348   0.01772   0.00877  -0.0936   0.8537   0.0670
  -3.250   0.0607   0.01725   0.00838  -0.0934   0.8459   0.1023
  -3.000   0.0881   0.01679   0.00797  -0.0932   0.8405   0.1368
  -2.750   0.1135   0.01646   0.00766  -0.0928   0.8322   0.1681
  -2.500   0.1406   0.01610   0.00731  -0.0924   0.8264   0.2041
  -2.250   0.1663   0.01581   0.00711  -0.0921   0.8185   0.2455
  -2.000   0.1929   0.01549   0.00688  -0.0917   0.8123   0.2963
  -1.750   0.2188   0.01520   0.00673  -0.0913   0.8050   0.3574
  -1.500   0.2445   0.01487   0.00659  -0.0907   0.7982   0.4346
  -1.250   0.2695   0.01450   0.00651  -0.0900   0.7914   0.5343
  -1.000   0.2919   0.01407   0.00647  -0.0883   0.7841   0.6638
  -0.750   0.3182   0.01350   0.00631  -0.0866   0.7785   0.8663
  -0.500   0.3586   0.01342   0.00611  -0.0890   0.7706   1.0000
  -0.250   0.3859   0.01345   0.00593  -0.0886   0.7647   1.0000
   0.000   0.4119   0.01359   0.00594  -0.0883   0.7558   1.0000
   0.250   0.4393   0.01363   0.00581  -0.0879   0.7498   1.0000
   0.500   0.4654   0.01378   0.00587  -0.0876   0.7408   1.0000
   0.750   0.4928   0.01383   0.00578  -0.0873   0.7347   1.0000
   1.000   0.5189   0.01399   0.00588  -0.0870   0.7255   1.0000
   1.250   0.5461   0.01406   0.00584  -0.0866   0.7188   1.0000
   1.500   0.5724   0.01421   0.00594  -0.0863   0.7096   1.0000
   1.750   0.5993   0.01431   0.00597  -0.0859   0.7019   1.0000
   2.000   0.6259   0.01443   0.00605  -0.0855   0.6931   1.0000
   2.250   0.6523   0.01456   0.00616  -0.0852   0.6842   1.0000
   2.500   0.6794   0.01464   0.00617  -0.0848   0.6758   1.0000
   2.750   0.7053   0.01479   0.00632  -0.0844   0.6649   1.0000
   3.000   0.7317   0.01490   0.00642  -0.0839   0.6545   1.0000
   3.250   0.7585   0.01498   0.00646  -0.0834   0.6444   1.0000
   3.500   0.7844   0.01512   0.00661  -0.0829   0.6324   1.0000
   3.750   0.8102   0.01527   0.00678  -0.0825   0.6203   1.0000
   4.000   0.8362   0.01541   0.00696  -0.0820   0.6080   1.0000
   4.250   0.8621   0.01556   0.00711  -0.0814   0.5953   1.0000
   4.500   0.8878   0.01572   0.00728  -0.0809   0.5820   1.0000
   4.750   0.9133   0.01589   0.00748  -0.0803   0.5677   1.0000
   5.000   0.9385   0.01609   0.00772  -0.0797   0.5526   1.0000
   5.250   0.9633   0.01630   0.00798  -0.0791   0.5363   1.0000
   5.500   0.9879   0.01654   0.00824  -0.0784   0.5189   1.0000
   5.750   1.0121   0.01680   0.00854  -0.0777   0.5003   1.0000
   6.000   1.0358   0.01709   0.00884  -0.0769   0.4802   1.0000
   6.250   1.0588   0.01743   0.00921  -0.0760   0.4577   1.0000
   6.500   1.0811   0.01782   0.00959  -0.0751   0.4338   1.0000
   6.750   1.1026   0.01828   0.01004  -0.0741   0.4081   1.0000
   7.000   1.1232   0.01882   0.01054  -0.0730   0.3803   1.0000
   7.250   1.1426   0.01943   0.01110  -0.0718   0.3512   1.0000
   7.500   1.1609   0.02014   0.01174  -0.0705   0.3218   1.0000
   7.750   1.1780   0.02093   0.01248  -0.0691   0.2929   1.0000
   8.000   1.1942   0.02179   0.01327  -0.0676   0.2653   1.0000
   8.250   1.2095   0.02270   0.01414  -0.0661   0.2401   1.0000
   8.500   1.2236   0.02369   0.01506  -0.0645   0.2176   1.0000
   8.750   1.2375   0.02466   0.01604  -0.0629   0.1961   1.0000
   9.000   1.2496   0.02573   0.01711  -0.0611   0.1773   1.0000
   9.250   1.2606   0.02681   0.01820  -0.0592   0.1595   1.0000
   9.500   1.2692   0.02795   0.01936  -0.0570   0.1425   1.0000
   9.750   1.2755   0.02928   0.02063  -0.0548   0.1241   1.0000
  10.000   1.2814   0.03072   0.02203  -0.0529   0.1057   1.0000
  10.250   1.2870   0.03226   0.02353  -0.0511   0.0891   1.0000
  10.500   1.2919   0.03395   0.02523  -0.0494   0.0759   1.0000
  10.750   1.2963   0.03575   0.02708  -0.0478   0.0658   1.0000
  11.000   1.2990   0.03778   0.02914  -0.0462   0.0573   1.0000
  11.500   1.3017   0.04233   0.03382  -0.0437   0.0437   1.0000
  11.750   1.2996   0.04506   0.03659  -0.0426   0.0398   1.0000
  12.000   1.2996   0.04772   0.03942  -0.0417   0.0363   1.0000
  12.250   1.2977   0.05066   0.04248  -0.0410   0.0339   1.0000
  12.500   1.2930   0.05401   0.04589  -0.0406   0.0323   1.0000
  12.750   1.2923   0.05706   0.04915  -0.0402   0.0307   1.0000
  13.000   1.2913   0.06024   0.05250  -0.0399   0.0293   1.0000
  13.250   1.2897   0.06356   0.05597  -0.0399   0.0279   1.0000
  13.500   1.2873   0.06706   0.05960  -0.0403   0.0267   1.0000
  13.750   1.2835   0.07083   0.06347  -0.0408   0.0258   1.0000
  14.000   1.2803   0.07465   0.06739  -0.0413   0.0250   1.0000
  14.250   1.2788   0.07847   0.07145  -0.0419   0.0241   1.0000
  14.500   1.2762   0.08253   0.07572  -0.0427   0.0234   1.0000
  14.750   1.2729   0.08680   0.08019  -0.0437   0.0228   1.0000
  15.000   1.2686   0.09136   0.08495  -0.0450   0.0223   1.0000
  15.250   1.2630   0.09628   0.09007  -0.0466   0.0220   1.0000
  15.500   1.2564   0.10150   0.09549  -0.0486   0.0217   1.0000
  15.750   1.2485   0.10713   0.10132  -0.0511   0.0214   1.0000
  16.000   1.2391   0.11325   0.10763  -0.0540   0.0212   1.0000
  16.250   1.2281   0.11995   0.11453  -0.0575   0.0211   1.0000
  16.500   1.2150   0.12739   0.12218  -0.0618   0.0210   1.0000
  16.750   1.1993   0.13586   0.13086  -0.0669   0.0210   1.0000
  17.000   1.1787   0.14618   0.14141  -0.0734   0.0212   1.0000
  17.250   1.1470   0.16076   0.15621  -0.0830   0.0217   1.0000
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