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S3016-095-87 (s3016-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S3016-095-87 (s3016-il)
Reynolds number: 50,000
Max Cl/Cd: 34.93 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3016-il-50000-n5.txt
Download as CSV file: xf-s3016-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3016-095-87                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4879   0.08952   0.08287  -0.0269   1.0000   0.0437
  -8.750  -0.4868   0.08519   0.07859  -0.0289   1.0000   0.0434
  -8.500  -0.4886   0.08046   0.07394  -0.0318   1.0000   0.0430
  -8.250  -0.4933   0.07553   0.06906  -0.0351   1.0000   0.0426
  -8.000  -0.4978   0.07069   0.06422  -0.0377   1.0000   0.0422
  -7.750  -0.5027   0.06583   0.05929  -0.0400   1.0000   0.0420
  -7.500  -0.5060   0.06116   0.05449  -0.0416   1.0000   0.0419
  -7.250  -0.5076   0.05661   0.04972  -0.0424   1.0000   0.0422
  -7.000  -0.5069   0.05238   0.04516  -0.0425   1.0000   0.0428
  -6.750  -0.5042   0.04851   0.04084  -0.0417   1.0000   0.0436
  -6.500  -0.4989   0.04507   0.03710  -0.0404   1.0000   0.0445
  -6.250  -0.4906   0.04232   0.03417  -0.0388   1.0000   0.0458
  -6.000  -0.4808   0.03956   0.03105  -0.0370   1.0000   0.0466
  -5.750  -0.4692   0.03702   0.02817  -0.0352   1.0000   0.0475
  -5.500  -0.4558   0.03467   0.02547  -0.0333   1.0000   0.0487
  -5.250  -0.4407   0.03265   0.02309  -0.0315   1.0000   0.0513
  -5.000  -0.4239   0.03090   0.02085  -0.0298   1.0000   0.0553
  -4.750  -0.4067   0.02913   0.01892  -0.0282   1.0000   0.0586
  -4.500  -0.3884   0.02765   0.01728  -0.0266   1.0000   0.0616
  -4.250  -0.3692   0.02633   0.01574  -0.0250   1.0000   0.0653
  -4.000  -0.3499   0.02514   0.01431  -0.0233   1.0000   0.0703
  -3.750  -0.3313   0.02423   0.01333  -0.0220   1.0000   0.0806
  -3.500  -0.3114   0.02327   0.01232  -0.0208   1.0000   0.0942
  -3.250  -0.2904   0.02219   0.01132  -0.0199   1.0000   0.1180
  -3.000  -0.2592   0.02088   0.01059  -0.0216   0.9944   0.2192
  -2.750  -0.2284   0.01976   0.01035  -0.0231   0.9866   0.3923
  -2.500  -0.1995   0.01901   0.01022  -0.0231   0.9784   0.5477
  -2.250  -0.1694   0.01850   0.01023  -0.0224   0.9711   0.7069
  -2.000  -0.1003   0.01826   0.01011  -0.0284   0.9699   0.9149
  -1.750  -0.0352   0.01830   0.00966  -0.0361   0.9653   1.0000
  -1.500   0.0060   0.01846   0.00945  -0.0394   0.9560   1.0000
  -1.250   0.0425   0.01861   0.00931  -0.0417   0.9450   1.0000
  -1.000   0.0798   0.01877   0.00919  -0.0441   0.9342   1.0000
  -0.750   0.1190   0.01892   0.00912  -0.0467   0.9242   1.0000
  -0.500   0.1593   0.01906   0.00907  -0.0493   0.9144   1.0000
  -0.250   0.1915   0.01922   0.00907  -0.0503   0.9021   1.0000
   0.000   0.2230   0.01937   0.00910  -0.0511   0.8896   1.0000
   0.250   0.2538   0.01953   0.00915  -0.0517   0.8768   1.0000
   0.500   0.2836   0.01967   0.00920  -0.0519   0.8636   1.0000
   0.750   0.3124   0.01980   0.00926  -0.0519   0.8500   1.0000
   1.000   0.3402   0.01992   0.00932  -0.0516   0.8360   1.0000
   1.250   0.3671   0.02002   0.00938  -0.0510   0.8213   1.0000
   1.500   0.3935   0.02009   0.00942  -0.0503   0.8061   1.0000
   1.750   0.4196   0.02014   0.00944  -0.0494   0.7904   1.0000
   2.000   0.4454   0.02017   0.00945  -0.0484   0.7744   1.0000
   2.250   0.4710   0.02017   0.00945  -0.0472   0.7583   1.0000
   2.500   0.4934   0.02027   0.00956  -0.0458   0.7394   1.0000
   2.750   0.5174   0.02030   0.00961  -0.0444   0.7211   1.0000
   3.000   0.5424   0.02028   0.00962  -0.0431   0.7031   1.0000
   3.250   0.5656   0.02035   0.00971  -0.0417   0.6825   1.0000
   3.500   0.5899   0.02036   0.00973  -0.0403   0.6618   1.0000
   3.750   0.6134   0.02044   0.00982  -0.0388   0.6393   1.0000
   4.000   0.6379   0.02047   0.00988  -0.0374   0.6166   1.0000
   4.250   0.6610   0.02063   0.01005  -0.0360   0.5910   1.0000
   4.500   0.6841   0.02082   0.01023  -0.0346   0.5643   1.0000
   4.750   0.7071   0.02106   0.01044  -0.0332   0.5365   1.0000
   5.000   0.7297   0.02137   0.01077  -0.0318   0.5079   1.0000
   5.250   0.7518   0.02176   0.01111  -0.0305   0.4787   1.0000
   5.500   0.7736   0.02222   0.01152  -0.0291   0.4498   1.0000
   5.750   0.7949   0.02276   0.01202  -0.0279   0.4214   1.0000
   6.000   0.8159   0.02337   0.01260  -0.0266   0.3942   1.0000
   6.250   0.8367   0.02405   0.01330  -0.0254   0.3682   1.0000
   6.500   0.8573   0.02478   0.01401  -0.0243   0.3443   1.0000
   6.750   0.8775   0.02556   0.01477  -0.0231   0.3212   1.0000
   7.000   0.8976   0.02640   0.01566  -0.0221   0.2994   1.0000
   7.250   0.9173   0.02728   0.01653  -0.0209   0.2791   1.0000
   7.500   0.9370   0.02822   0.01753  -0.0199   0.2599   1.0000
   7.750   0.9559   0.02920   0.01866  -0.0187   0.2411   1.0000
   8.000   0.9745   0.03024   0.01975  -0.0176   0.2240   1.0000
   8.250   0.9926   0.03131   0.02087  -0.0165   0.2080   1.0000
   8.500   1.0102   0.03248   0.02214  -0.0153   0.1927   1.0000
   8.750   1.0266   0.03370   0.02350  -0.0140   0.1777   1.0000
   9.000   1.0431   0.03501   0.02492  -0.0128   0.1646   1.0000
   9.250   1.0576   0.03634   0.02636  -0.0115   0.1517   1.0000
   9.500   1.0711   0.03778   0.02800  -0.0101   0.1396   1.0000
   9.750   1.0836   0.03943   0.02988  -0.0086   0.1282   1.0000
  10.000   1.0931   0.04113   0.03178  -0.0070   0.1173   1.0000
  10.250   1.1020   0.04296   0.03377  -0.0054   0.1080   1.0000
  10.500   1.1087   0.04459   0.03536  -0.0037   0.0993   1.0000
  10.750   1.1085   0.04682   0.03797  -0.0016   0.0910   1.0000
  11.000   1.1099   0.04896   0.04018   0.0002   0.0844   1.0000
  11.250   1.1061   0.05149   0.04297   0.0018   0.0780   1.0000
  11.500   1.1041   0.05401   0.04553   0.0030   0.0726   1.0000
  11.750   1.0960   0.05760   0.04947   0.0038   0.0682   1.0000
  12.000   1.0908   0.06043   0.05235   0.0041   0.0638   1.0000
  12.250   1.0827   0.06423   0.05629   0.0039   0.0607   1.0000
  12.500   1.0668   0.06941   0.06181   0.0027   0.0587   1.0000
  12.750   1.0500   0.07509   0.06775   0.0007   0.0575   1.0000
  13.000   1.0303   0.08170   0.07459  -0.0024   0.0569   1.0000
  13.250   1.0063   0.08979   0.08289  -0.0068   0.0573   1.0000
  13.500   0.9792   0.09940   0.09266  -0.0124   0.0587   1.0000
  13.750   0.9519   0.11003   0.10336  -0.0186   0.0603   1.0000
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