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FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il)
Reynolds number: 50,000
Max Cl/Cd: 27.18 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx711520-il-50000.txt
Download as CSV file: xf-fx711520-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/20 AIRFOIL                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6790   0.10377   0.09656  -0.0093   1.0000   0.1221
 -11.500  -0.7944   0.08350   0.07613  -0.0246   1.0000   0.1121
 -11.250  -0.8144   0.07766   0.07022  -0.0267   1.0000   0.1108
 -11.000  -0.8428   0.07209   0.06450  -0.0284   1.0000   0.1096
 -10.750  -0.8695   0.06748   0.05971  -0.0286   1.0000   0.1083
 -10.500  -0.8926   0.06344   0.05542  -0.0275   1.0000   0.1072
 -10.250  -0.9045   0.05944   0.05111  -0.0265   1.0000   0.1066
 -10.000  -0.9075   0.05572   0.04705  -0.0255   1.0000   0.1064
  -9.750  -0.9027   0.05225   0.04326  -0.0247   1.0000   0.1070
  -9.500  -0.8921   0.04903   0.03974  -0.0240   1.0000   0.1082
  -9.250  -0.8782   0.04597   0.03632  -0.0233   1.0000   0.1104
  -9.000  -0.8623   0.04308   0.03300  -0.0225   1.0000   0.1134
  -8.750  -0.8327   0.04060   0.03066  -0.0229   1.0000   0.1205
  -8.500  -0.8058   0.03822   0.02829  -0.0228   1.0000   0.1304
  -8.250  -0.7774   0.03598   0.02613  -0.0227   1.0000   0.1463
  -8.000  -0.7559   0.03397   0.02440  -0.0221   1.0000   0.1707
  -7.750  -0.7431   0.03214   0.02292  -0.0209   1.0000   0.2024
  -7.500  -0.7329   0.03017   0.02137  -0.0191   1.0000   0.2438
  -7.250  -0.7309   0.02831   0.02019  -0.0160   1.0000   0.2962
  -7.000  -0.7387   0.02717   0.01977  -0.0110   1.0000   0.3579
  -6.750  -0.7426   0.02782   0.02111  -0.0045   1.0000   0.4308
  -6.500  -0.7320   0.03064   0.02413   0.0021   1.0000   0.4905
  -6.250  -0.7039   0.03481   0.02821   0.0080   1.0000   0.5290
  -6.000  -0.6478   0.04075   0.03392   0.0131   1.0000   0.5591
  -5.750  -0.6469   0.04160   0.03467   0.0183   1.0000   0.5830
  -5.500  -0.6196   0.04387   0.03678   0.0226   1.0000   0.6064
  -5.250  -0.5450   0.04743   0.04001   0.0234   1.0000   0.6340
  -5.000  -0.5222   0.04797   0.04040   0.0258   1.0000   0.6569
  -4.750  -0.5051   0.04802   0.04034   0.0282   1.0000   0.6784
  -4.500  -0.4879   0.04783   0.04003   0.0301   1.0000   0.6992
  -4.250  -0.4708   0.04749   0.03956   0.0318   1.0000   0.7194
  -4.000  -0.4546   0.04698   0.03894   0.0332   1.0000   0.7385
  -3.750  -0.4464   0.04631   0.03819   0.0353   1.0000   0.7556
  -3.500  -0.4870   0.04513   0.03704   0.0435   1.0000   0.7687
  -3.250  -0.4656   0.04449   0.03628   0.0438   1.0000   0.7842
  -3.000  -0.4384   0.04386   0.03552   0.0431   1.0000   0.7999
  -2.750  -0.4128   0.04319   0.03475   0.0423   0.9995   0.8151
  -2.500  -0.3589   0.04266   0.03405   0.0362   0.9932   0.8304
  -2.250  -0.3415   0.04192   0.03320   0.0353   0.9858   0.8423
  -2.000  -0.2800   0.04150   0.03264   0.0278   0.9796   0.8552
  -1.750  -0.2331   0.04098   0.03202   0.0227   0.9729   0.8670
  -1.500  -0.2104   0.04061   0.03157   0.0210   0.9663   0.8776
  -1.250  -0.1591   0.04014   0.03103   0.0150   0.9594   0.8865
  -1.000  -0.1277   0.03989   0.03072   0.0119   0.9530   0.8951
  -0.750  -0.1042   0.03957   0.03037   0.0104   0.9469   0.9023
  -0.500  -0.0669   0.03941   0.03018   0.0065   0.9405   0.9109
  -0.250  -0.0314   0.03938   0.03013   0.0029   0.9341   0.9194
   0.000   0.0001   0.03927   0.03002   0.0000   0.9266   0.9267
   0.250   0.0321   0.03938   0.03013  -0.0030   0.9193   0.9342
   0.500   0.0666   0.03941   0.03018  -0.0065   0.9110   0.9405
   0.750   0.1037   0.03956   0.03036  -0.0103   0.9024   0.9469
   1.000   0.1279   0.03988   0.03071  -0.0120   0.8951   0.9530
   1.250   0.1597   0.04013   0.03102  -0.0151   0.8866   0.9595
   1.500   0.2110   0.04061   0.03157  -0.0211   0.8777   0.9664
   1.750   0.2323   0.04097   0.03201  -0.0226   0.8673   0.9729
   2.000   0.2800   0.04149   0.03263  -0.0278   0.8553   0.9795
   2.250   0.3431   0.04189   0.03318  -0.0356   0.8422   0.9859
   2.500   0.3593   0.04264   0.03403  -0.0363   0.8304   0.9932
   2.750   0.4131   0.04317   0.03472  -0.0423   0.8149   0.9995
   3.000   0.4387   0.04384   0.03550  -0.0431   0.7999   1.0000
   3.250   0.4670   0.04447   0.03626  -0.0440   0.7844   1.0000
   3.500   0.4802   0.04520   0.03709  -0.0427   0.7693   1.0000
   3.750   0.4461   0.04629   0.03817  -0.0353   0.7557   1.0000
   4.000   0.4544   0.04697   0.03894  -0.0332   0.7386   1.0000
   4.250   0.4711   0.04747   0.03954  -0.0318   0.7194   1.0000
   4.500   0.4883   0.04781   0.03999  -0.0302   0.6991   1.0000
   4.750   0.5049   0.04801   0.04032  -0.0282   0.6785   1.0000
   5.000   0.5223   0.04795   0.04038  -0.0258   0.6570   1.0000
   5.250   0.5445   0.04743   0.04001  -0.0233   0.6342   1.0000
   5.500   0.6193   0.04387   0.03678  -0.0225   0.6064   1.0000
   5.750   0.6472   0.04156   0.03463  -0.0183   0.5830   1.0000
   6.000   0.6479   0.04073   0.03391  -0.0131   0.5591   1.0000
   6.250   0.7035   0.03484   0.02824  -0.0080   0.5291   1.0000
   6.500   0.7325   0.03056   0.02405  -0.0020   0.4903   1.0000
   6.750   0.7425   0.02781   0.02110   0.0045   0.4309   1.0000
   7.000   0.7386   0.02717   0.01977   0.0110   0.3579   1.0000
   7.250   0.7309   0.02831   0.02019   0.0160   0.2961   1.0000
   7.500   0.7327   0.03017   0.02138   0.0191   0.2434   1.0000
   7.750   0.7425   0.03214   0.02291   0.0209   0.2019   1.0000
   8.000   0.7560   0.03397   0.02440   0.0221   0.1707   1.0000
   8.250   0.7775   0.03598   0.02613   0.0227   0.1463   1.0000
   8.500   0.8057   0.03822   0.02829   0.0228   0.1301   1.0000
   8.750   0.8326   0.04061   0.03067   0.0229   0.1203   1.0000
   9.000   0.8629   0.04311   0.03302   0.0225   0.1133   1.0000
   9.250   0.8783   0.04598   0.03634   0.0233   0.1103   1.0000
   9.500   0.8923   0.04904   0.03975   0.0239   0.1082   1.0000
   9.750   0.9029   0.05226   0.04327   0.0247   0.1070   1.0000
  10.000   0.9078   0.05574   0.04707   0.0255   0.1063   1.0000
  10.250   0.9048   0.05946   0.05113   0.0265   0.1066   1.0000
  10.500   0.8927   0.06348   0.05546   0.0275   0.1072   1.0000
  10.750   0.8700   0.06749   0.05972   0.0286   0.1083   1.0000
  11.000   0.8431   0.07213   0.06454   0.0283   0.1096   1.0000
  11.250   0.8151   0.07768   0.07023   0.0266   0.1108   1.0000
  11.500   0.7960   0.08347   0.07610   0.0245   0.1122   1.0000
  11.750   0.6791   0.10396   0.09676   0.0090   0.1221   1.0000
  12.000   0.6820   0.10955   0.10232   0.0073   0.1242   1.0000
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