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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 100,000
Max Cl/Cd: 41.09 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4095-il-100000.txt
Download as CSV file: xf-s4095-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4095 (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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5982   0.11993   0.11522   0.0243   1.0007   0.0884
  -8.500  -0.6084   0.11587   0.11123   0.0197   1.0007   0.0910
  -8.250  -0.6134   0.11133   0.10675   0.0171   1.0007   0.0921
  -8.000  -0.5986   0.10760   0.10301   0.0190   1.0007   0.0949
  -7.750  -0.6011   0.10327   0.09871   0.0145   1.0007   0.0984
  -7.500  -0.5999   0.09755   0.09300   0.0073   1.0007   0.1007
  -7.250  -0.5873   0.09405   0.08952   0.0088   1.0007   0.1039
  -7.000  -0.5791   0.08722   0.08258  -0.0033   1.0007   0.1096
  -6.750  -0.5652   0.08403   0.07945  -0.0004   1.0007   0.1126
  -6.500  -0.5480   0.07781   0.07307  -0.0094   1.0007   0.1202
  -6.250  -0.5311   0.07445   0.06973  -0.0088   1.0007   0.1249
  -6.000  -0.4999   0.06893   0.06365  -0.0218   1.0007   0.1420
  -5.750  -0.4858   0.06478   0.05978  -0.0182   1.0007   0.1448
  -5.500  -0.4615   0.06092   0.05582  -0.0210   1.0007   0.1584
  -5.250  -0.4352   0.05716   0.05193  -0.0238   1.0007   0.1731
  -5.000  -0.3608   0.03844   0.03109  -0.0387   1.0007   0.0782
  -4.750  -0.3232   0.03323   0.02502  -0.0406   1.0007   0.0692
  -4.500  -0.2893   0.02993   0.02119  -0.0416   1.0007   0.0673
  -4.250  -0.2565   0.02746   0.01827  -0.0423   1.0007   0.0680
  -4.000  -0.2248   0.02559   0.01609  -0.0429   1.0007   0.0719
  -3.750  -0.1937   0.02392   0.01425  -0.0432   1.0007   0.0757
  -3.500  -0.1633   0.02233   0.01265  -0.0435   1.0007   0.0808
  -3.250  -0.1328   0.02105   0.01133  -0.0437   1.0007   0.0916
  -3.000  -0.1030   0.01970   0.01027  -0.0442   1.0007   0.1148
  -2.750  -0.0729   0.01832   0.00930  -0.0448   1.0007   0.1824
  -2.500  -0.0441   0.01713   0.00881  -0.0455   1.0007   0.3007
  -2.250  -0.0206   0.01529   0.00855  -0.0446   1.0007   0.6178
  -2.000  -0.0017   0.01343   0.00745  -0.0409   1.0007   0.9993
  -1.750   0.0285   0.01353   0.00724  -0.0417   1.0007   0.9993
  -1.500   0.0584   0.01370   0.00719  -0.0425   1.0007   0.9993
  -1.250   0.0876   0.01395   0.00729  -0.0434   1.0007   0.9993
  -1.000   0.1156   0.01440   0.00760  -0.0442   1.0007   0.9993
  -0.750   0.1404   0.01524   0.00834  -0.0449   1.0007   0.9993
  -0.500   0.1822   0.01557   0.00853  -0.0488   0.9925   0.9993
  -0.250   0.2351   0.01530   0.00810  -0.0544   0.9699   0.9993
   0.000   0.2810   0.01522   0.00788  -0.0581   0.9414   0.9993
   0.250   0.3144   0.01541   0.00792  -0.0587   0.9089   0.9993
   0.500   0.3397   0.01571   0.00809  -0.0574   0.8769   0.9993
   0.750   0.3637   0.01603   0.00827  -0.0559   0.8484   0.9993
   1.000   0.3881   0.01634   0.00843  -0.0546   0.8224   0.9993
   1.250   0.4133   0.01663   0.00860  -0.0535   0.7974   0.9993
   1.500   0.4389   0.01692   0.00877  -0.0526   0.7739   0.9993
   1.750   0.4651   0.01721   0.00893  -0.0518   0.7512   0.9993
   2.000   0.4917   0.01750   0.00912  -0.0512   0.7291   0.9993
   2.250   0.5187   0.01779   0.00930  -0.0507   0.7073   0.9993
   2.500   0.5459   0.01809   0.00949  -0.0502   0.6857   0.9993
   2.750   0.5733   0.01838   0.00968  -0.0499   0.6643   0.9993
   3.000   0.6009   0.01868   0.00989  -0.0496   0.6429   0.9993
   3.250   0.6286   0.01898   0.01013  -0.0493   0.6215   0.9993
   3.500   0.6564   0.01928   0.01036  -0.0491   0.6000   0.9993
   3.750   0.6842   0.01959   0.01060  -0.0490   0.5785   0.9993
   4.000   0.7121   0.01990   0.01084  -0.0489   0.5570   0.9993
   4.250   0.7401   0.02022   0.01113  -0.0487   0.5353   0.9993
   4.500   0.7680   0.02054   0.01139  -0.0487   0.5135   0.9993
   4.750   0.7959   0.02087   0.01166  -0.0486   0.4918   0.9993
   5.000   0.8238   0.02123   0.01195  -0.0486   0.4701   0.9993
   5.250   0.8516   0.02163   0.01230  -0.0485   0.4486   0.9993
   5.500   0.8796   0.02205   0.01272  -0.0486   0.4260   0.9993
   5.750   0.9075   0.02250   0.01317  -0.0487   0.4034   0.9993
   6.000   0.9353   0.02300   0.01367  -0.0488   0.3812   0.9993
   6.250   0.9628   0.02354   0.01418  -0.0489   0.3596   0.9993
   6.500   0.9902   0.02412   0.01472  -0.0490   0.3386   0.9993
   6.750   1.0175   0.02476   0.01533  -0.0490   0.3182   0.9993
   7.000   1.0445   0.02546   0.01599  -0.0491   0.2985   0.9993
   7.250   1.0714   0.02622   0.01674  -0.0492   0.2791   0.9993
   7.500   1.0982   0.02699   0.01759  -0.0494   0.2597   0.9993
   7.750   1.1247   0.02783   0.01848  -0.0494   0.2412   0.9993
   8.000   1.1509   0.02872   0.01941  -0.0495   0.2237   0.9993
   8.250   1.1767   0.02967   0.02041  -0.0495   0.2070   0.9993
   8.500   1.2021   0.03069   0.02147  -0.0495   0.1915   0.9993
   8.750   1.2272   0.03180   0.02260  -0.0494   0.1770   0.9993
   9.000   1.2519   0.03299   0.02385  -0.0494   0.1636   0.9993
   9.250   1.2762   0.03428   0.02520  -0.0492   0.1512   0.9993
   9.500   1.3001   0.03568   0.02667  -0.0490   0.1398   0.9993
   9.750   1.3234   0.03717   0.02824  -0.0488   0.1292   0.9993
  10.000   1.3461   0.03873   0.02989  -0.0485   0.1193   0.9993
  10.250   1.3675   0.04026   0.03148  -0.0481   0.1091   0.9993
  10.500   1.3843   0.04137   0.03290  -0.0474   0.0972   0.9993
  10.750   1.4016   0.04224   0.03366  -0.0469   0.0864   0.9993
  11.000   1.4141   0.04400   0.03579  -0.0457   0.0760   0.9993
  11.250   1.4254   0.04592   0.03779  -0.0444   0.0664   0.9993
  11.500   1.4334   0.04806   0.04003  -0.0428   0.0580   0.9993
  11.750   1.4402   0.05083   0.04292  -0.0411   0.0519   0.9993
  12.000   1.4468   0.05378   0.04601  -0.0393   0.0477   0.9993
  12.250   1.4452   0.05728   0.04991  -0.0368   0.0450   0.9993
  12.500   1.4449   0.06067   0.05350  -0.0347   0.0431   0.9993
  12.750   1.4291   0.06456   0.05777  -0.0315   0.0421   0.9993
  13.000   1.4178   0.06826   0.06168  -0.0295   0.0410   0.9993
  13.250   1.4152   0.07162   0.06509  -0.0286   0.0396   0.9993
  13.500   1.3931   0.07713   0.07096  -0.0286   0.0393   0.9993
  13.750   1.3709   0.08333   0.07749  -0.0300   0.0392   0.9993
  14.000   1.3488   0.09011   0.08457  -0.0325   0.0392   0.9993
  14.250   1.3260   0.09753   0.09225  -0.0360   0.0392   0.9993
  14.500   1.3036   0.10540   0.10035  -0.0402   0.0394   0.9993
  14.750   1.2821   0.11358   0.10872  -0.0449   0.0397   0.9993
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