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S4110 (s4110-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 50,000
Max Cl/Cd: 39.24 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4110-il-50000.txt
Download as CSV file: xf-s4110-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4022   0.10652   0.09968  -0.0240   1.0000   0.2053
  -8.000  -0.3727   0.10025   0.09335  -0.0218   1.0000   0.2154
  -7.750  -0.4010   0.10090   0.09424  -0.0226   1.0000   0.2199
  -7.500  -0.3756   0.09544   0.08874  -0.0207   1.0000   0.2317
  -7.250  -0.3741   0.09253   0.08592  -0.0196   1.0000   0.2399
  -7.000  -0.3929   0.09193   0.08551  -0.0184   1.0000   0.2485
  -6.750  -0.3861   0.08871   0.08235  -0.0164   1.0000   0.2618
  -6.500  -0.3830   0.08585   0.07957  -0.0145   1.0000   0.2742
  -6.250  -0.3840   0.08336   0.07719  -0.0128   1.0000   0.2872
  -6.000  -0.3864   0.08102   0.07495  -0.0109   1.0000   0.3015
  -5.750  -0.3893   0.07870   0.07271  -0.0089   1.0000   0.3156
  -5.500  -0.3917   0.07641   0.07051  -0.0067   1.0000   0.3314
  -5.250  -0.3966   0.07437   0.06858  -0.0047   1.0000   0.3497
  -4.750  -0.3973   0.06954   0.06391   0.0013   1.0000   0.3891
  -4.500  -0.4010   0.06746   0.06191   0.0043   1.0000   0.4152
  -4.250  -0.3210   0.04620   0.03906  -0.0474   1.0000   0.1510
  -4.000  -0.2917   0.04095   0.03318  -0.0508   1.0000   0.1394
  -3.750  -0.2644   0.03727   0.02896  -0.0526   1.0000   0.1420
  -3.500  -0.2342   0.03377   0.02472  -0.0542   1.0000   0.1449
  -3.250  -0.2090   0.03144   0.02212  -0.0544   1.0000   0.1573
  -3.000  -0.1819   0.02929   0.01959  -0.0547   1.0000   0.1727
  -2.750  -0.1541   0.02750   0.01736  -0.0548   1.0000   0.1909
  -2.500  -0.1300   0.02612   0.01596  -0.0543   1.0000   0.2119
  -2.250  -0.1042   0.02498   0.01454  -0.0540   1.0000   0.2345
  -2.000  -0.0807   0.02396   0.01358  -0.0533   1.0000   0.2597
  -1.750  -0.0560   0.02310   0.01274  -0.0527   1.0000   0.2963
  -1.500  -0.0304   0.02216   0.01205  -0.0523   1.0000   0.3575
  -1.250  -0.0083   0.02013   0.01162  -0.0503   1.0000   0.6037
  -1.000   0.0029   0.01896   0.01088  -0.0460   1.0000   1.0000
  -0.750   0.0262   0.01932   0.01075  -0.0461   1.0000   1.0000
  -0.500   0.0483   0.01972   0.01080  -0.0459   1.0000   1.0000
  -0.250   0.0698   0.02016   0.01093  -0.0458   1.0000   1.0000
   0.000   0.0908   0.02065   0.01118  -0.0456   1.0000   1.0000
   0.250   0.1114   0.02118   0.01150  -0.0454   1.0000   1.0000
   0.500   0.1316   0.02176   0.01190  -0.0453   1.0000   1.0000
   0.750   0.1512   0.02238   0.01236  -0.0452   1.0000   1.0000
   1.000   0.1705   0.02306   0.01292  -0.0451   1.0000   1.0000
   1.250   0.1894   0.02380   0.01355  -0.0450   1.0000   1.0000
   1.500   0.2079   0.02460   0.01426  -0.0450   1.0000   1.0000
   1.750   0.2422   0.02578   0.01535  -0.0480   0.9920   1.0000
   2.000   0.2947   0.02721   0.01673  -0.0541   0.9737   1.0000
   2.250   0.3462   0.02850   0.01799  -0.0598   0.9549   1.0000
   2.500   0.3915   0.02951   0.01901  -0.0640   0.9343   1.0000
   2.750   0.4454   0.03050   0.02003  -0.0693   0.9144   1.0000
   3.000   0.4852   0.03120   0.02081  -0.0720   0.8916   1.0000
   3.250   0.5416   0.03170   0.02142  -0.0767   0.8703   1.0000
   3.500   0.5803   0.03209   0.02192  -0.0784   0.8457   1.0000
   3.750   0.6277   0.03216   0.02217  -0.0808   0.8218   1.0000
   4.000   0.6893   0.03147   0.02170  -0.0844   0.7987   1.0000
   4.250   0.7351   0.03081   0.02128  -0.0851   0.7722   1.0000
   4.500   0.7817   0.02974   0.02040  -0.0852   0.7453   1.0000
   4.750   0.8275   0.02835   0.01921  -0.0846   0.7165   1.0000
   5.000   0.8714   0.02680   0.01786  -0.0832   0.6845   1.0000
   5.250   0.9050   0.02580   0.01693  -0.0808   0.6459   1.0000
   5.500   0.9360   0.02504   0.01614  -0.0782   0.6018   1.0000
   5.750   0.9639   0.02473   0.01569  -0.0756   0.5528   1.0000
   6.000   0.9858   0.02512   0.01586  -0.0729   0.5003   1.0000
   6.250   1.0085   0.02584   0.01624  -0.0706   0.4508   1.0000
   6.500   1.0293   0.02695   0.01709  -0.0686   0.4054   1.0000
   6.750   1.0499   0.02825   0.01820  -0.0668   0.3658   1.0000
   7.000   1.0715   0.02974   0.01956  -0.0654   0.3321   1.0000
   7.250   1.0925   0.03130   0.02106  -0.0640   0.3024   1.0000
   7.500   1.1156   0.03300   0.02258  -0.0629   0.2766   1.0000
   7.750   1.1339   0.03481   0.02459  -0.0613   0.2534   1.0000
   8.000   1.1568   0.03680   0.02646  -0.0604   0.2331   1.0000
   8.250   1.1733   0.03895   0.02893  -0.0587   0.2147   1.0000
   8.500   1.1915   0.04148   0.03167  -0.0573   0.1998   1.0000
   8.750   1.2074   0.04390   0.03430  -0.0558   0.1851   1.0000
   9.000   1.2239   0.04687   0.03747  -0.0544   0.1743   1.0000
   9.250   1.2428   0.04970   0.04032  -0.0533   0.1630   1.0000
   9.500   1.2406   0.05330   0.04465  -0.0503   0.1560   1.0000
   9.750   1.2571   0.05676   0.04815  -0.0492   0.1485   1.0000
  10.000   1.2467   0.06140   0.05349  -0.0463   0.1460   1.0000
  10.250   1.2334   0.06609   0.05865  -0.0437   0.1437   1.0000
  10.500   1.2167   0.07085   0.06375  -0.0414   0.1421   1.0000
  10.750   1.2076   0.07487   0.06795  -0.0397   0.1387   1.0000
  11.000   1.1900   0.07937   0.07261  -0.0379   0.1376   1.0000
  11.250   1.1743   0.08423   0.07758  -0.0368   0.1365   1.0000
  11.500   0.9920   0.11622   0.10940  -0.0601   0.1797   1.0000
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