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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 50,000
Max Cl/Cd: 31.34 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4096-il-50000-n5.txt
Download as CSV file: xf-s4096-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4096 (designed for the E-flite UMX ASK-21 scale
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6522   0.11127   0.10434   0.0016   1.0011   0.0530
  -9.000  -0.6600   0.10528   0.09840  -0.0016   1.0011   0.0521
  -8.750  -0.6654   0.09809   0.09120  -0.0067   1.0011   0.0511
  -8.500  -0.6692   0.09012   0.08314  -0.0120   1.0011   0.0499
  -8.250  -0.6705   0.08154   0.07434  -0.0173   1.0011   0.0486
  -8.000  -0.6657   0.07293   0.06530  -0.0223   1.0011   0.0475
  -7.750  -0.6523   0.06533   0.05710  -0.0263   1.0011   0.0468
  -7.500  -0.6320   0.05937   0.05055  -0.0291   1.0011   0.0467
  -7.250  -0.6085   0.05546   0.04628  -0.0308   1.0011   0.0478
  -7.000  -0.5829   0.05190   0.04232  -0.0324   1.0011   0.0497
  -6.750  -0.5551   0.04822   0.03810  -0.0340   1.0011   0.0516
  -6.500  -0.5258   0.04472   0.03399  -0.0352   1.0011   0.0528
  -6.250  -0.4960   0.04167   0.03043  -0.0361   1.0011   0.0538
  -6.000  -0.4659   0.03908   0.02736  -0.0366   1.0011   0.0552
  -5.750  -0.4365   0.03684   0.02483  -0.0370   1.0011   0.0569
  -5.500  -0.4084   0.03513   0.02309  -0.0375   1.0011   0.0605
  -5.250  -0.3795   0.03365   0.02139  -0.0378   1.0011   0.0659
  -5.000  -0.3509   0.03215   0.01977  -0.0379   1.0011   0.0709
  -4.750  -0.3222   0.03082   0.01837  -0.0382   1.0011   0.0777
  -4.500  -0.2934   0.02955   0.01706  -0.0385   1.0011   0.0899
  -4.250  -0.2640   0.02822   0.01583  -0.0392   1.0011   0.1203
  -4.000  -0.2351   0.02663   0.01494  -0.0403   1.0011   0.2180
  -3.750  -0.2083   0.02541   0.01457  -0.0409   1.0011   0.3824
  -3.250  -0.1612   0.02379   0.01400  -0.0385   1.0011   0.6310
  -3.000  -0.1431   0.02304   0.01373  -0.0349   1.0011   0.7711
  -2.750  -0.1082   0.02198   0.01281  -0.0352   1.0011   0.9800
  -2.500  -0.0793   0.02170   0.01220  -0.0362   1.0011   0.9989
  -2.250  -0.0515   0.02181   0.01201  -0.0369   1.0011   0.9989
  -2.000  -0.0242   0.02200   0.01196  -0.0374   1.0011   0.9989
  -1.750   0.0024   0.02230   0.01203  -0.0379   1.0011   0.9989
  -1.500   0.0283   0.02270   0.01225  -0.0382   1.0011   0.9989
  -1.250   0.0531   0.02324   0.01264  -0.0385   1.0011   0.9989
  -1.000   0.0770   0.02392   0.01319  -0.0386   1.0011   0.9989
  -0.750   0.0996   0.02478   0.01394  -0.0387   1.0011   0.9989
  -0.500   0.1411   0.02488   0.01387  -0.0425   0.9898   0.9989
  -0.250   0.1875   0.02468   0.01352  -0.0471   0.9744   0.9989
   0.000   0.2325   0.02452   0.01323  -0.0513   0.9577   0.9989
   0.250   0.2749   0.02441   0.01301  -0.0548   0.9383   0.9989
   0.500   0.3159   0.02435   0.01285  -0.0579   0.9185   0.9989
   0.750   0.3546   0.02435   0.01276  -0.0602   0.8986   0.9989
   1.000   0.3885   0.02446   0.01279  -0.0615   0.8757   0.9989
   1.250   0.4205   0.02461   0.01286  -0.0621   0.8543   0.9989
   1.500   0.4499   0.02484   0.01302  -0.0623   0.8322   0.9989
   1.750   0.4784   0.02509   0.01320  -0.0622   0.8111   0.9989
   2.000   0.5061   0.02536   0.01340  -0.0618   0.7909   0.9989
   2.250   0.5336   0.02565   0.01366  -0.0616   0.7700   0.9989
   2.500   0.5608   0.02594   0.01391  -0.0612   0.7502   0.9989
   2.750   0.5880   0.02624   0.01415  -0.0608   0.7311   0.9989
   3.000   0.6154   0.02656   0.01448  -0.0606   0.7107   0.9989
   3.250   0.6427   0.02688   0.01478  -0.0603   0.6911   0.9989
   3.500   0.6699   0.02719   0.01507  -0.0600   0.6721   0.9989
   3.750   0.6973   0.02753   0.01542  -0.0599   0.6517   0.9989
   4.000   0.7246   0.02787   0.01580  -0.0597   0.6314   0.9989
   4.250   0.7519   0.02820   0.01612  -0.0594   0.6118   0.9989
   4.500   0.7792   0.02857   0.01654  -0.0593   0.5905   0.9989
   4.750   0.8064   0.02893   0.01695  -0.0592   0.5695   0.9989
   5.000   0.8336   0.02931   0.01735  -0.0590   0.5484   0.9989
   5.250   0.8609   0.02971   0.01782  -0.0590   0.5260   0.9989
   5.500   0.8880   0.03012   0.01827  -0.0588   0.5043   0.9989
   5.750   0.9150   0.03057   0.01880  -0.0588   0.4810   0.9989
   6.000   0.9418   0.03104   0.01929  -0.0587   0.4586   0.9989
   6.250   0.9684   0.03156   0.01985  -0.0586   0.4352   0.9989
   6.500   0.9947   0.03213   0.02049  -0.0585   0.4122   0.9989
   6.750   1.0207   0.03275   0.02113  -0.0584   0.3895   0.9989
   7.000   1.0465   0.03346   0.02190  -0.0583   0.3665   0.9989
   7.250   1.0718   0.03420   0.02266  -0.0582   0.3445   0.9989
   7.500   1.0969   0.03504   0.02361  -0.0581   0.3223   0.9989
   7.750   1.1214   0.03592   0.02452  -0.0579   0.3010   0.9989
   8.000   1.1455   0.03689   0.02557  -0.0578   0.2805   0.9989
   8.250   1.1690   0.03793   0.02670  -0.0576   0.2604   0.9989
   8.500   1.1918   0.03903   0.02787  -0.0573   0.2421   0.9989
   8.750   1.2140   0.04023   0.02915  -0.0570   0.2244   0.9989
   9.000   1.2357   0.04153   0.03059  -0.0566   0.2073   0.9989
   9.250   1.2562   0.04291   0.03209  -0.0561   0.1914   0.9989
   9.500   1.2760   0.04438   0.03369  -0.0555   0.1770   0.9989
   9.750   1.2945   0.04595   0.03542  -0.0548   0.1635   0.9989
  10.000   1.3122   0.04762   0.03721  -0.0540   0.1517   0.9989
  10.250   1.3283   0.04933   0.03898  -0.0530   0.1409   0.9989
  10.500   1.3432   0.05125   0.04115  -0.0519   0.1306   0.9989
  10.750   1.3563   0.05338   0.04353  -0.0506   0.1214   0.9989
  11.000   1.3683   0.05539   0.04557  -0.0493   0.1139   0.9989
  11.250   1.3773   0.05793   0.04852  -0.0476   0.1065   0.9989
  11.500   1.3850   0.06025   0.05091  -0.0459   0.1004   0.9989
  11.750   1.3864   0.06324   0.05429  -0.0437   0.0945   0.9989
  12.000   1.3910   0.06559   0.05664  -0.0418   0.0898   0.9989
  12.250   1.3812   0.06937   0.06084  -0.0388   0.0859   0.9989
  12.500   1.3677   0.07327   0.06504  -0.0360   0.0827   0.9989
  12.750   1.3590   0.07682   0.06872  -0.0344   0.0793   0.9989
  13.000   1.3527   0.08061   0.07259  -0.0334   0.0762   0.9989
  13.250   1.3314   0.08678   0.07917  -0.0334   0.0745   0.9989
  13.500   1.3094   0.09355   0.08629  -0.0347   0.0729   0.9989
  13.750   1.2860   0.10110   0.09413  -0.0372   0.0717   0.9989
  14.000   1.2587   0.11007   0.10337  -0.0411   0.0712   0.9989
  14.250   1.2215   0.12218   0.11574  -0.0478   0.0723   0.9989
  14.500   1.1743   0.13862   0.13233  -0.0578   0.0742   0.9989
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