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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 1,000,000
Max Cl/Cd: 65.55 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4096-il-1000000.txt
Download as CSV file: xf-s4096-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7241   0.10273   0.10122   0.0122   1.0011   0.0132
  -9.500  -0.8317   0.05629   0.05421  -0.0172   1.0011   0.0115
  -9.250  -0.8392   0.03728   0.03382  -0.0228   1.0011   0.0111
  -9.000  -0.8136   0.03423   0.03039  -0.0239   1.0011   0.0116
  -8.750  -0.7865   0.03193   0.02777  -0.0248   1.0011   0.0119
  -8.500  -0.7584   0.03019   0.02577  -0.0256   1.0011   0.0120
  -8.250  -0.7297   0.02907   0.02439  -0.0264   1.0011   0.0123
  -8.000  -0.7019   0.02552   0.02048  -0.0275   1.0011   0.0125
  -7.750  -0.6733   0.02358   0.01838  -0.0284   1.0011   0.0128
  -7.500  -0.6441   0.02255   0.01728  -0.0291   1.0011   0.0131
  -7.250  -0.6147   0.02173   0.01640  -0.0299   1.0011   0.0134
  -7.000  -0.5850   0.02111   0.01573  -0.0306   1.0011   0.0139
  -6.750  -0.5552   0.02051   0.01508  -0.0313   1.0011   0.0144
  -6.500  -0.5253   0.01985   0.01436  -0.0320   1.0011   0.0148
  -6.250  -0.4952   0.01924   0.01368  -0.0327   1.0011   0.0152
  -6.000  -0.4651   0.01869   0.01309  -0.0334   1.0011   0.0155
  -5.750  -0.4349   0.01824   0.01259  -0.0341   1.0011   0.0157
  -5.500  -0.4046   0.01786   0.01218  -0.0348   1.0011   0.0159
  -5.250  -0.3741   0.01701   0.01127  -0.0357   1.0011   0.0164
  -5.000  -0.3434   0.01650   0.01072  -0.0365   1.0011   0.0170
  -4.750  -0.3129   0.01618   0.01040  -0.0373   1.0011   0.0179
  -4.500  -0.2823   0.01593   0.01014  -0.0381   1.0011   0.0187
  -4.250  -0.2516   0.01570   0.00989  -0.0389   1.0011   0.0195
  -4.000  -0.2208   0.01550   0.00968  -0.0397   1.0011   0.0201
  -3.750  -0.1900   0.01530   0.00946  -0.0405   1.0011   0.0210
  -3.500  -0.1577   0.01526   0.00941  -0.0417   0.9935   0.0231
  -3.250  -0.1259   0.01533   0.00945  -0.0425   0.9534   0.0258
  -3.000  -0.1006   0.01526   0.00944  -0.0418   0.9099   0.0594
  -2.750  -0.0727   0.01506   0.00941  -0.0419   0.8754   0.1325
  -2.500  -0.0435   0.01489   0.00942  -0.0425   0.8456   0.2123
  -2.250  -0.0139   0.01478   0.00943  -0.0431   0.8185   0.2811
  -2.000   0.0160   0.01471   0.00944  -0.0438   0.7933   0.3350
  -1.750   0.0462   0.01464   0.00946  -0.0446   0.7705   0.3928
  -1.500   0.0765   0.01455   0.00951  -0.0454   0.7490   0.4631
  -1.250   0.1068   0.01444   0.00961  -0.0463   0.7293   0.5555
  -1.000   0.1371   0.01426   0.00984  -0.0472   0.7110   0.6947
  -0.500   0.1860   0.01340   0.00968  -0.0451   0.6786   0.9989
  -0.250   0.2166   0.01344   0.00962  -0.0459   0.6627   0.9989
   0.000   0.2473   0.01348   0.00956  -0.0467   0.6474   0.9989
   0.250   0.2779   0.01353   0.00951  -0.0475   0.6331   0.9989
   0.500   0.3084   0.01357   0.00947  -0.0482   0.6190   0.9989
   0.750   0.3390   0.01361   0.00943  -0.0490   0.6052   0.9989
   1.000   0.3695   0.01366   0.00940  -0.0498   0.5912   0.9989
   1.250   0.4000   0.01371   0.00938  -0.0505   0.5776   0.9989
   1.500   0.4304   0.01376   0.00937  -0.0513   0.5639   0.9989
   1.750   0.4609   0.01382   0.00936  -0.0520   0.5499   0.9989
   2.000   0.4913   0.01388   0.00935  -0.0528   0.5352   0.9989
   2.250   0.5216   0.01394   0.00935  -0.0535   0.5200   0.9989
   2.500   0.5519   0.01402   0.00935  -0.0543   0.5033   0.9989
   2.750   0.5822   0.01409   0.00936  -0.0550   0.4859   0.9989
   3.000   0.6124   0.01417   0.00937  -0.0558   0.4674   0.9989
   3.250   0.6425   0.01427   0.00939  -0.0565   0.4474   0.9989
   3.500   0.6725   0.01438   0.00941  -0.0573   0.4275   0.9989
   3.750   0.7026   0.01449   0.00944  -0.0580   0.4072   0.9989
   4.000   0.7325   0.01462   0.00949  -0.0587   0.3870   0.9989
   4.250   0.7624   0.01477   0.00955  -0.0595   0.3669   0.9989
   4.500   0.7922   0.01491   0.00962  -0.0602   0.3469   0.9989
   4.750   0.8220   0.01507   0.00970  -0.0609   0.3276   0.9989
   5.000   0.8517   0.01526   0.00980  -0.0616   0.3085   0.9989
   5.250   0.8814   0.01543   0.00991  -0.0623   0.2902   0.9989
   5.500   0.9110   0.01562   0.01004  -0.0630   0.2725   0.9989
   5.750   0.9404   0.01584   0.01018  -0.0637   0.2538   0.9989
   6.000   0.9698   0.01606   0.01033  -0.0644   0.2370   0.9989
   6.250   0.9991   0.01631   0.01051  -0.0651   0.2188   0.9989
   6.500   1.0283   0.01657   0.01069  -0.0658   0.2002   0.9989
   6.750   1.0574   0.01683   0.01089  -0.0664   0.1839   0.9989
   7.000   1.0865   0.01710   0.01111  -0.0671   0.1698   0.9989
   7.250   1.1154   0.01740   0.01135  -0.0677   0.1555   0.9989
   7.500   1.1441   0.01773   0.01161  -0.0683   0.1399   0.9989
   7.750   1.1727   0.01810   0.01190  -0.0689   0.1243   0.9989
   8.000   1.2012   0.01847   0.01220  -0.0695   0.1111   0.9989
   8.250   1.2296   0.01883   0.01252  -0.0701   0.0995   0.9989
   8.500   1.2577   0.01924   0.01286  -0.0706   0.0870   0.9989
   8.750   1.2857   0.01965   0.01323  -0.0712   0.0763   0.9989
   9.000   1.3137   0.02004   0.01360  -0.0717   0.0678   0.9989
   9.250   1.3413   0.02050   0.01401  -0.0722   0.0590   0.9989
   9.500   1.3686   0.02100   0.01446  -0.0726   0.0505   0.9989
   9.750   1.3960   0.02143   0.01489  -0.0730   0.0450   0.9989
  10.000   1.4232   0.02190   0.01536  -0.0734   0.0394   0.9989
  10.250   1.4498   0.02246   0.01589  -0.0738   0.0337   0.9989
  10.500   1.4765   0.02295   0.01638  -0.0741   0.0293   0.9989
  10.750   1.5024   0.02357   0.01698  -0.0744   0.0240   0.9989
  11.000   1.5270   0.02443   0.01777  -0.0744   0.0158   0.9989
  11.250   1.5507   0.02540   0.01871  -0.0744   0.0097   0.9989
  11.500   1.5749   0.02621   0.01956  -0.0744   0.0080   0.9989
  11.750   1.5982   0.02714   0.02054  -0.0742   0.0070   0.9989
  12.000   1.6218   0.02792   0.02139  -0.0740   0.0066   0.9989
  12.250   1.6448   0.02873   0.02228  -0.0738   0.0062   0.9989
  12.500   1.6669   0.02962   0.02325  -0.0735   0.0059   0.9989
  12.750   1.6875   0.03063   0.02434  -0.0729   0.0056   0.9989
  13.000   1.7061   0.03183   0.02563  -0.0721   0.0053   0.9989
  13.250   1.7212   0.03336   0.02728  -0.0708   0.0051   0.9989
  13.500   1.7343   0.03493   0.02898  -0.0693   0.0049   0.9989
  13.750   1.7484   0.03624   0.03038  -0.0678   0.0049   0.9989
  14.000   1.7589   0.03773   0.03198  -0.0659   0.0048   0.9989
  14.250   1.7643   0.03950   0.03387  -0.0632   0.0047   0.9989
  14.500   1.7515   0.04206   0.03657  -0.0576   0.0047   0.9989
  14.750   1.7413   0.04509   0.03973  -0.0538   0.0046   0.9989
  15.000   1.7334   0.04854   0.04332  -0.0515   0.0046   0.9989
  15.250   1.7257   0.05244   0.04737  -0.0502   0.0045   0.9989
  15.500   1.7171   0.05687   0.05194  -0.0497   0.0045   0.9989
  15.750   1.7070   0.06180   0.05702  -0.0498   0.0044   0.9989
  16.000   1.6946   0.06732   0.06269  -0.0506   0.0044   0.9989
  16.250   1.6803   0.07332   0.06885  -0.0518   0.0044   0.9989
  16.500   1.6632   0.07991   0.07559  -0.0534   0.0043   0.9989
  16.750   1.6435   0.08704   0.08288  -0.0554   0.0043   0.9989
  17.000   1.6218   0.09460   0.09059  -0.0578   0.0043   0.9989
  17.250   1.5993   0.10259   0.09874  -0.0607   0.0043   0.9989
  17.500   1.5769   0.11088   0.10718  -0.0640   0.0043   0.9989
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