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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 50,000
Max Cl/Cd: 38.72 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4062-il-50000.txt
Download as CSV file: xf-s4062-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3296   0.10479   0.09861  -0.0290   1.0000   0.2004
  -7.750  -0.3520   0.10502   0.09899  -0.0264   1.0000   0.2049
  -7.500  -0.3830   0.10609   0.10022  -0.0233   1.0000   0.2062
  -7.250  -0.3631   0.10084   0.09497  -0.0213   1.0000   0.2130
  -7.000  -0.3815   0.10033   0.09457  -0.0183   1.0000   0.2183
  -6.750  -0.4145   0.10113   0.09555  -0.0157   1.0000   0.2208
  -6.500  -0.4075   0.09736   0.09182  -0.0129   1.0000   0.2260
  -6.250  -0.4183   0.09596   0.09049  -0.0111   1.0000   0.2334
  -6.000  -0.4351   0.09440   0.08905  -0.0110   1.0000   0.2383
  -5.750  -0.4311   0.09159   0.08627  -0.0080   1.0000   0.2469
  -5.500  -0.4413   0.08946   0.08422  -0.0081   1.0000   0.2543
  -5.250  -0.4513   0.08810   0.08290  -0.0107   1.0000   0.2667
  -5.000  -0.4425   0.08451   0.07936  -0.0050   1.0000   0.2766
  -4.750  -0.4433   0.08197   0.07687  -0.0038   1.0000   0.2913
  -4.500  -0.4461   0.07993   0.07483  -0.0062   1.0000   0.3116
  -4.250  -0.4431   0.07696   0.07190  -0.0041   1.0000   0.3284
  -4.000  -0.4387   0.07414   0.06912  -0.0011   1.0000   0.3457
  -3.750  -0.4339   0.07150   0.06651   0.0011   1.0000   0.3670
  -3.500  -0.2977   0.04773   0.04055  -0.0529   1.0000   0.1307
  -3.250  -0.2671   0.04324   0.03559  -0.0557   1.0000   0.1242
  -3.000  -0.2360   0.03980   0.03157  -0.0579   1.0000   0.1258
  -2.750  -0.2037   0.03681   0.02782  -0.0596   1.0000   0.1304
  -2.500  -0.1769   0.03470   0.02542  -0.0601   1.0000   0.1392
  -2.250  -0.1496   0.03297   0.02333  -0.0604   1.0000   0.1550
  -2.000  -0.1230   0.03156   0.02162  -0.0605   1.0000   0.1806
  -1.750  -0.0985   0.03051   0.02052  -0.0602   1.0000   0.2164
  -1.500  -0.0743   0.02965   0.01965  -0.0599   1.0000   0.2640
  -1.250  -0.0490   0.02896   0.01903  -0.0596   1.0000   0.3255
  -1.000  -0.0232   0.02830   0.01866  -0.0594   1.0000   0.4084
  -0.750   0.0025   0.02729   0.01848  -0.0587   1.0000   0.5647
  -0.500   0.0144   0.02564   0.01771  -0.0553   1.0000   1.0000
  -0.250   0.0384   0.02626   0.01771  -0.0557   1.0000   1.0000
   0.000   0.0603   0.02690   0.01794  -0.0558   1.0000   1.0000
   0.250   0.0814   0.02757   0.01827  -0.0558   1.0000   1.0000
   0.500   0.1021   0.02828   0.01870  -0.0558   1.0000   1.0000
   0.750   0.1223   0.02903   0.01921  -0.0558   1.0000   1.0000
   1.000   0.1422   0.02981   0.01978  -0.0557   1.0000   1.0000
   1.250   0.1618   0.03064   0.02042  -0.0557   1.0000   1.0000
   1.500   0.1809   0.03151   0.02113  -0.0557   1.0000   1.0000
   1.750   0.2094   0.03276   0.02222  -0.0575   0.9956   1.0000
   2.000   0.2545   0.03457   0.02385  -0.0624   0.9810   1.0000
   2.250   0.2936   0.03615   0.02532  -0.0660   0.9666   1.0000
   2.500   0.3314   0.03767   0.02675  -0.0693   0.9515   1.0000
   2.750   0.3684   0.03915   0.02816  -0.0723   0.9356   1.0000
   3.000   0.4057   0.04060   0.02957  -0.0752   0.9192   1.0000
   3.250   0.4467   0.04210   0.03105  -0.0785   0.9019   1.0000
   3.500   0.4786   0.04331   0.03228  -0.0802   0.8842   1.0000
   3.750   0.5080   0.04442   0.03341  -0.0814   0.8657   1.0000
   4.000   0.5438   0.04555   0.03459  -0.0832   0.8466   1.0000
   4.250   0.5886   0.04664   0.03576  -0.0861   0.8278   1.0000
   4.500   0.6110   0.04753   0.03672  -0.0859   0.8075   1.0000
   4.750   0.6469   0.04831   0.03760  -0.0871   0.7875   1.0000
   5.000   0.6903   0.04886   0.03831  -0.0889   0.7685   1.0000
   5.250   0.7126   0.04957   0.03913  -0.0883   0.7465   1.0000
   5.500   0.7578   0.04959   0.03932  -0.0896   0.7270   1.0000
   5.750   0.7827   0.05005   0.03991  -0.0888   0.7046   1.0000
   6.000   0.8276   0.04948   0.03960  -0.0893   0.6845   1.0000
   6.250   0.8580   0.04932   0.03963  -0.0884   0.6619   1.0000
   6.500   0.9075   0.04765   0.03828  -0.0882   0.6415   1.0000
   6.750   0.9464   0.04625   0.03713  -0.0869   0.6190   1.0000
   7.000   1.0139   0.04194   0.03325  -0.0862   0.5990   1.0000
   7.250   1.0737   0.03799   0.02965  -0.0850   0.5729   1.0000
   7.500   1.1463   0.03301   0.02492  -0.0844   0.5381   1.0000
   7.750   1.1847   0.03133   0.02319  -0.0823   0.4942   1.0000
   8.000   1.2093   0.03123   0.02291  -0.0798   0.4486   1.0000
   8.250   1.2302   0.03190   0.02333  -0.0774   0.4040   1.0000
   8.500   1.2494   0.03308   0.02426  -0.0752   0.3617   1.0000
   8.750   1.2644   0.03468   0.02571  -0.0729   0.3234   1.0000
   9.000   1.2804   0.03649   0.02732  -0.0709   0.2875   1.0000
   9.250   1.2935   0.03849   0.02924  -0.0686   0.2552   1.0000
   9.500   1.3076   0.04069   0.03136  -0.0666   0.2257   1.0000
   9.750   1.3209   0.04301   0.03362  -0.0645   0.1994   1.0000
  10.000   1.3349   0.04527   0.03572  -0.0628   0.1751   1.0000
  10.250   1.3399   0.04777   0.03845  -0.0600   0.1569   1.0000
  10.500   1.3481   0.05041   0.04119  -0.0577   0.1405   1.0000
  10.750   1.3558   0.05346   0.04441  -0.0556   0.1278   1.0000
  11.000   1.3641   0.05686   0.04798  -0.0537   0.1181   1.0000
  11.250   1.3815   0.06037   0.05141  -0.0529   0.1082   1.0000
  11.500   1.3689   0.06422   0.05585  -0.0493   0.1063   1.0000
  11.750   1.3535   0.06808   0.06015  -0.0458   0.1050   1.0000
  12.000   1.3345   0.07209   0.06452  -0.0427   0.1043   1.0000
  12.250   1.3126   0.07645   0.06919  -0.0404   0.1040   1.0000
  12.500   1.2879   0.08132   0.07435  -0.0389   0.1043   1.0000
  12.750   1.2610   0.08683   0.08010  -0.0386   0.1049   1.0000
  13.000   1.2336   0.09299   0.08646  -0.0393   0.1058   1.0000
  13.250   1.2064   0.09985   0.09348  -0.0410   0.1067   1.0000
  13.500   1.1817   0.10730   0.10104  -0.0437   0.1076   1.0000
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