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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 50,000
Max Cl/Cd: 39.23 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-50000-n5.txt
Download as CSV file: xf-s1221-flap-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1221  w/ 4 deg flap                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2782   0.10221   0.09586  -0.0243   1.0000   0.0619
  -7.000  -0.2794   0.09964   0.09339  -0.0236   1.0000   0.0607
  -6.500  -0.3090   0.09232   0.08632  -0.0253   1.0000   0.0545
  -6.250  -0.3069   0.08971   0.08380  -0.0247   1.0000   0.0541
  -6.000  -0.3054   0.08688   0.08105  -0.0247   1.0000   0.0536
  -5.750  -0.3035   0.08391   0.07818  -0.0251   1.0000   0.0529
  -5.500  -0.3012   0.08044   0.07480  -0.0266   1.0000   0.0521
  -5.250  -0.2971   0.07638   0.07084  -0.0295   1.0000   0.0512
  -5.000  -0.2848   0.07070   0.06522  -0.0361   0.9989   0.0501
  -4.750  -0.1662   0.04452   0.03758  -0.0922   0.9971   0.0461
  -4.500  -0.0919   0.03900   0.03141  -0.1068   0.9912   0.0469
  -4.250  -0.0272   0.03566   0.02764  -0.1165   0.9829   0.0488
  -4.000   0.0353   0.03303   0.02448  -0.1247   0.9724   0.0531
  -3.750   0.0898   0.03101   0.02225  -0.1303   0.9593   0.0572
  -3.500   0.1421   0.02932   0.02038  -0.1349   0.9440   0.0618
  -3.250   0.1969   0.02765   0.01865  -0.1404   0.9263   0.0721
  -3.000   0.2522   0.02582   0.01685  -0.1464   0.9018   0.0935
  -2.750   0.3145   0.02429   0.01629  -0.1544   0.8671   0.2708
  -2.500   0.3367   0.02499   0.01703  -0.1520   0.8033   0.3363
  -2.250   0.3858   0.02508   0.01691  -0.1527   0.7622   0.3890
  -2.000   0.4668   0.02423   0.01522  -0.1610   0.7189   0.4160
  -1.750   0.5244   0.02404   0.01431  -0.1661   0.6763   0.4312
  -1.500   0.5614   0.02417   0.01403  -0.1673   0.6441   0.4403
  -1.250   0.5999   0.02425   0.01370  -0.1695   0.6174   0.4503
  -1.000   0.6325   0.02442   0.01357  -0.1702   0.5965   0.4585
  -0.750   0.6684   0.02457   0.01339  -0.1718   0.5783   0.4678
  -0.500   0.7010   0.02475   0.01334  -0.1727   0.5627   0.4758
  -0.250   0.7354   0.02495   0.01330  -0.1740   0.5490   0.4857
   0.000   0.7686   0.02517   0.01333  -0.1749   0.5372   0.4958
   0.250   0.8014   0.02540   0.01340  -0.1758   0.5258   0.5055
   0.500   0.8350   0.02565   0.01352  -0.1770   0.5152   0.5175
   0.750   0.8674   0.02592   0.01366  -0.1777   0.5065   0.5298
   1.000   0.8986   0.02620   0.01395  -0.1784   0.4975   0.5430
   1.250   0.9308   0.02651   0.01417  -0.1791   0.4900   0.5578
   1.500   0.9609   0.02685   0.01454  -0.1795   0.4821   0.5742
   1.750   0.9907   0.02720   0.01490  -0.1797   0.4749   0.5931
   2.000   1.0202   0.02758   0.01529  -0.1800   0.4686   0.6147
   2.250   1.0473   0.02800   0.01583  -0.1797   0.4620   0.6378
   2.500   1.0742   0.02840   0.01631  -0.1793   0.4565   0.6645
   2.750   1.0998   0.02885   0.01683  -0.1787   0.4512   0.6956
   3.000   1.1240   0.02933   0.01746  -0.1779   0.4451   0.7328
   3.250   1.1490   0.02975   0.01793  -0.1772   0.4400   0.7778
   3.500   1.1711   0.03003   0.01825  -0.1758   0.4361   0.8285
   3.750   1.1835   0.03019   0.01870  -0.1727   0.4311   1.0000
   4.000   1.2159   0.03104   0.01951  -0.1741   0.4255   1.0000
   4.250   1.2478   0.03181   0.02017  -0.1751   0.4209   1.0000
   4.500   1.2762   0.03273   0.02115  -0.1756   0.4162   1.0000
   4.750   1.3024   0.03373   0.02225  -0.1757   0.4110   1.0000
   5.000   1.3299   0.03460   0.02314  -0.1759   0.4064   1.0000
   5.250   1.3591   0.03539   0.02389  -0.1762   0.4026   1.0000
   5.500   1.3812   0.03661   0.02532  -0.1757   0.3975   1.0000
   5.750   1.4044   0.03775   0.02661  -0.1753   0.3927   1.0000
   6.000   1.4300   0.03870   0.02764  -0.1751   0.3885   1.0000
   6.250   1.4583   0.03951   0.02840  -0.1752   0.3850   1.0000
   6.500   1.4735   0.04117   0.03042  -0.1738   0.3793   1.0000
   6.750   1.4942   0.04244   0.03186  -0.1731   0.3744   1.0000
   7.000   1.5193   0.04336   0.03284  -0.1727   0.3704   1.0000
   7.250   1.5392   0.04468   0.03433  -0.1718   0.3657   1.0000
   7.500   1.5516   0.04654   0.03650  -0.1702   0.3600   1.0000
   7.750   1.5729   0.04764   0.03774  -0.1693   0.3552   1.0000
   8.000   1.6014   0.04820   0.03828  -0.1692   0.3513   1.0000
   8.250   1.6001   0.05105   0.04160  -0.1662   0.3446   1.0000
   8.500   1.6169   0.05235   0.04307  -0.1649   0.3393   1.0000
   8.750   1.6479   0.05253   0.04325  -0.1649   0.3351   1.0000
   9.000   1.6341   0.05626   0.04746  -0.1609   0.3281   1.0000
   9.250   1.6481   0.05760   0.04896  -0.1593   0.3225   1.0000
   9.500   1.6770   0.05773   0.04915  -0.1589   0.3179   1.0000
   9.750   1.6394   0.06317   0.05505  -0.1533   0.3110   1.0000
  10.000   1.6539   0.06421   0.05624  -0.1516   0.3056   1.0000
  10.250   1.6606   0.06581   0.05798  -0.1494   0.3006   1.0000
  10.500   1.4840   0.08722   0.07974  -0.1449   0.2919   1.0000
  10.750   1.5422   0.08241   0.07504  -0.1422   0.2886   1.0000
  11.000   1.4112   0.10762   0.10034  -0.1519   0.2730   1.0000
  11.250   1.4502   0.10407   0.09692  -0.1484   0.2708   1.0000
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