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FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il)
Reynolds number: 100,000
Max Cl/Cd: 13.26 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s171-il-100000.txt
Download as CSV file: xf-fx66s171-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-171 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2561   0.09573   0.09186  -0.0722   0.9338   0.1594
  -9.750  -0.1960   0.09131   0.08722  -0.0740   0.9142   0.1664
  -9.500  -0.3680   0.05575   0.05108  -0.1096   0.8928   0.0702
  -9.250  -0.3734   0.05117   0.04618  -0.1112   0.8724   0.0675
  -9.000  -0.3869   0.04655   0.04097  -0.1112   0.8555   0.0638
  -8.750  -0.3941   0.04350   0.03698  -0.1097   0.8411   0.0607
  -8.500  -0.3808   0.04123   0.03426  -0.1089   0.8296   0.0603
  -8.250  -0.3669   0.03823   0.03084  -0.1081   0.8194   0.0604
  -8.000  -0.3514   0.03505   0.02750  -0.1077   0.8091   0.0626
  -7.750  -0.3309   0.03342   0.02571  -0.1071   0.8003   0.0656
  -7.500  -0.3111   0.03176   0.02375  -0.1062   0.7912   0.0684
  -7.250  -0.2893   0.03018   0.02181  -0.1052   0.7833   0.0712
  -7.000  -0.2667   0.02846   0.01999  -0.1046   0.7758   0.0761
  -6.750  -0.2434   0.02735   0.01879  -0.1039   0.7694   0.0825
  -6.500  -0.2209   0.02611   0.01753  -0.1031   0.7624   0.0896
  -6.250  -0.1972   0.02526   0.01655  -0.1022   0.7572   0.0999
  -6.000  -0.1785   0.02430   0.01579  -0.1010   0.7504   0.1133
  -5.750  -0.1608   0.02324   0.01492  -0.0997   0.7447   0.1343
  -5.500  -0.1462   0.02175   0.01381  -0.0984   0.7399   0.1906
  -5.250  -0.1373   0.02086   0.01420  -0.0962   0.7338   0.4123
  -5.000  -0.1128   0.02199   0.01519  -0.0946   0.7289   0.4695
  -4.750  -0.0874   0.02297   0.01603  -0.0931   0.7250   0.5000
  -4.500  -0.0658   0.02375   0.01675  -0.0917   0.7192   0.5229
  -4.250  -0.0416   0.02453   0.01751  -0.0899   0.7145   0.5421
  -4.000  -0.0164   0.02517   0.01805  -0.0882   0.7108   0.5612
  -3.750   0.0040   0.02581   0.01869  -0.0866   0.7059   0.5774
  -3.500   0.0258   0.02630   0.01914  -0.0851   0.7013   0.5928
  -3.250   0.0500   0.02654   0.01927  -0.0839   0.6975   0.6068
  -3.000   0.0752   0.02664   0.01922  -0.0832   0.6943   0.6193
  -2.750   0.0936   0.02698   0.01953  -0.0825   0.6892   0.6311
  -2.500   0.1154   0.02722   0.01973  -0.0815   0.6852   0.6397
  -2.250   0.1412   0.02716   0.01953  -0.0815   0.6819   0.6489
  -2.000   0.1689   0.02711   0.01932  -0.0815   0.6792   0.6577
  -1.750   0.1840   0.02765   0.01989  -0.0807   0.6738   0.6646
  -1.500   0.2054   0.02795   0.02014  -0.0804   0.6699   0.6722
  -1.250   0.2309   0.02803   0.02012  -0.0806   0.6669   0.6796
  -1.000   0.2592   0.02803   0.01999  -0.0807   0.6645   0.6865
  -0.750   0.2729   0.02887   0.02085  -0.0801   0.6594   0.6936
  -0.500   0.2897   0.02947   0.02147  -0.0792   0.6548   0.7002
  -0.250   0.3147   0.02975   0.02165  -0.0795   0.6518   0.7084
   0.000   0.3426   0.02980   0.02165  -0.0794   0.6494   0.7152
   0.250   0.3471   0.03135   0.02325  -0.0781   0.6435   0.7225
   0.500   0.3610   0.03215   0.02408  -0.0770   0.6385   0.7288
   0.750   0.3908   0.03219   0.02404  -0.0774   0.6355   0.7376
   1.000   0.4238   0.03196   0.02376  -0.0776   0.6334   0.7456
   1.250   0.3972   0.03533   0.02728  -0.0738   0.6239   0.7532
   1.500   0.4231   0.03550   0.02746  -0.0735   0.6207   0.7621
   1.750   0.4592   0.03522   0.02713  -0.0742   0.6187   0.7726
   2.000   0.3837   0.04120   0.03331  -0.0666   0.6080   0.7790
   2.250   0.4197   0.04102   0.03312  -0.0673   0.6051   0.7902
   2.500   0.4680   0.04030   0.03237  -0.0690   0.6033   0.8029
   2.750   0.3886   0.04669   0.03889  -0.0621   0.5938   0.8126
   3.000   0.4109   0.04741   0.03964  -0.0620   0.5904   0.8278
   3.250   0.4550   0.04683   0.03911  -0.0629   0.5880   0.8477
   4.000   0.4943   0.05245   0.04501  -0.0657   0.5731   1.0000
   4.250   0.4820   0.05598   0.04849  -0.0657   0.5670   1.0000
   4.500   0.4821   0.05884   0.05129  -0.0661   0.5640   1.0000
   4.750   0.5099   0.05984   0.05222  -0.0671   0.5596   1.0000
   5.000   0.4095   0.07105   0.06359  -0.0671   0.6099   1.0000
   5.250   0.4425   0.07255   0.06503  -0.0684   0.6045   1.0000
   5.500   0.4880   0.07485   0.06726  -0.0707   0.6021   1.0000
   5.750   0.4576   0.07619   0.06860  -0.0678   0.5926   1.0000
   6.000   0.4925   0.07794   0.07031  -0.0691   0.5885   1.0000
   6.250   0.4852   0.07984   0.07221  -0.0679   0.5807   1.0000
   6.500   0.5074   0.08148   0.07384  -0.0683   0.5752   1.0000
   6.750   0.5477   0.08361   0.07596  -0.0699   0.5722   1.0000
   7.000   0.5288   0.08523   0.07759  -0.0680   0.5621   1.0000
   7.250   0.5605   0.08708   0.07944  -0.0689   0.5581   1.0000
   7.500   0.5546   0.08927   0.08165  -0.0681   0.5510   1.0000
   7.750   0.5783   0.09085   0.08326  -0.0685   0.5442   1.0000
   8.000   0.6195   0.09320   0.08564  -0.0699   0.5415   1.0000
   8.250   0.5949   0.09501   0.08747  -0.0683   0.5314   1.0000
   8.500   0.6335   0.09694   0.08945  -0.0693   0.5272   1.0000
   8.750   0.6165   0.09930   0.09184  -0.0684   0.5189   1.0000
   9.000   0.6459   0.10106   0.09365  -0.0689   0.5133   1.0000
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