Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il)
Reynolds number: 500,000
Max Cl/Cd: 48.28 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx711525-il-500000-n5.txt
Download as CSV file: xf-fx711525-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/25 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -0.9957   0.14370   0.14027   0.0164   1.0000   0.0116
 -19.250  -1.0155   0.13464   0.13103   0.0108   1.0000   0.0115
 -19.000  -1.0284   0.12743   0.12369   0.0064   1.0000   0.0116
 -18.750  -1.0429   0.12006   0.11617   0.0020   1.0000   0.0115
 -18.500  -1.0542   0.11354   0.10951  -0.0018   1.0000   0.0115
 -18.250  -1.0653   0.10722   0.10306  -0.0054   1.0000   0.0115
 -18.000  -1.0749   0.10137   0.09708  -0.0086   1.0000   0.0115
 -17.750  -1.0819   0.09610   0.09168  -0.0114   1.0000   0.0115
 -17.500  -1.0895   0.09090   0.08637  -0.0141   1.0000   0.0115
 -17.250  -1.0947   0.08620   0.08156  -0.0164   1.0000   0.0115
 -17.000  -1.0999   0.08166   0.07690  -0.0185   1.0000   0.0115
 -16.750  -1.1038   0.07743   0.07257  -0.0204   1.0000   0.0116
 -16.500  -1.1064   0.07348   0.06851  -0.0221   1.0000   0.0115
 -16.250  -1.1087   0.06972   0.06465  -0.0236   1.0000   0.0116
 -16.000  -1.1097   0.06621   0.06104  -0.0249   1.0000   0.0115
 -15.750  -1.1108   0.06280   0.05754  -0.0260   1.0000   0.0116
 -15.500  -1.1099   0.05974   0.05438  -0.0269   1.0000   0.0116
 -15.250  -1.1088   0.05680   0.05137  -0.0277   1.0000   0.0117
 -15.000  -1.1068   0.05402   0.04850  -0.0283   1.0000   0.0116
 -14.750  -1.1041   0.05141   0.04581  -0.0288   1.0000   0.0116
 -14.500  -1.1012   0.04895   0.04328  -0.0291   1.0000   0.0117
 -14.250  -1.0980   0.04660   0.04085  -0.0293   1.0000   0.0117
 -14.000  -1.0936   0.04441   0.03859  -0.0294   1.0000   0.0117
 -13.750  -1.0895   0.04227   0.03638  -0.0294   1.0000   0.0118
 -13.500  -1.0843   0.04026   0.03430  -0.0293   1.0000   0.0118
 -13.250  -1.0786   0.03836   0.03234  -0.0290   1.0000   0.0119
 -13.000  -1.0462   0.03609   0.02991  -0.0345   0.8881   0.0119
 -12.750  -1.0329   0.03449   0.02803  -0.0353   0.8338   0.0120
 -12.500  -1.0267   0.03301   0.02641  -0.0345   0.8197   0.0120
 -12.250  -1.0196   0.03160   0.02490  -0.0336   0.8110   0.0120
 -12.000  -1.0115   0.03029   0.02349  -0.0327   0.8047   0.0121
 -11.750  -1.0030   0.02903   0.02215  -0.0318   0.7998   0.0122
 -11.500  -0.9950   0.02776   0.02080  -0.0307   0.7948   0.0123
 -11.000  -0.9768   0.02548   0.01837  -0.0284   0.7863   0.0124
 -10.750  -0.9675   0.02439   0.01721  -0.0272   0.7823   0.0125
 -10.500  -0.9569   0.02343   0.01618  -0.0259   0.7786   0.0126
 -10.250  -0.9474   0.02247   0.01515  -0.0245   0.7750   0.0126
 -10.000  -0.9370   0.02161   0.01424  -0.0229   0.7715   0.0126
  -9.750  -0.9275   0.02078   0.01336  -0.0210   0.7675   0.0127
  -9.500  -0.9173   0.02009   0.01260  -0.0189   0.7638   0.0128
  -9.250  -0.9059   0.01953   0.01199  -0.0167   0.7605   0.0128
  -9.000  -0.8915   0.01897   0.01137  -0.0149   0.7574   0.0129
  -8.750  -0.8741   0.01842   0.01078  -0.0136   0.7538   0.0130
  -8.500  -0.8555   0.01791   0.01023  -0.0125   0.7500   0.0130
  -8.250  -0.8359   0.01742   0.00970  -0.0114   0.7464   0.0132
  -8.000  -0.8156   0.01695   0.00919  -0.0105   0.7432   0.0133
  -7.750  -0.7948   0.01649   0.00868  -0.0095   0.7400   0.0134
  -7.500  -0.7731   0.01604   0.00820  -0.0088   0.7365   0.0137
  -7.250  -0.7506   0.01563   0.00776  -0.0081   0.7330   0.0139
  -7.000  -0.7275   0.01525   0.00735  -0.0074   0.7297   0.0142
  -6.750  -0.7039   0.01490   0.00696  -0.0069   0.7266   0.0145
  -6.500  -0.6800   0.01458   0.00660  -0.0063   0.7237   0.0149
  -6.250  -0.6555   0.01426   0.00626  -0.0059   0.7205   0.0155
  -6.000  -0.6308   0.01392   0.00594  -0.0054   0.7167   0.0168
  -5.750  -0.6064   0.01357   0.00561  -0.0050   0.7127   0.0215
  -5.500  -0.5811   0.01329   0.00532  -0.0046   0.7089   0.0273
  -5.250  -0.5562   0.01297   0.00502  -0.0042   0.7056   0.0331
  -5.000  -0.5316   0.01259   0.00471  -0.0038   0.7023   0.0490
  -4.500  -0.4809   0.01190   0.00417  -0.0032   0.6943   0.0820
  -4.250  -0.4563   0.01148   0.00388  -0.0028   0.6900   0.1086
  -4.000  -0.4323   0.01099   0.00356  -0.0024   0.6861   0.1506
  -3.750  -0.4095   0.01033   0.00321  -0.0018   0.6823   0.2181
  -3.500  -0.3856   0.00976   0.00291  -0.0014   0.6776   0.2787
  -3.250  -0.3610   0.00927   0.00264  -0.0010   0.6725   0.3345
  -3.000  -0.3366   0.00880   0.00241  -0.0006   0.6677   0.4001
  -2.750  -0.3112   0.00845   0.00227  -0.0002   0.6633   0.4525
  -2.500  -0.2842   0.00825   0.00221  -0.0001   0.6584   0.4891
  -2.250  -0.2563   0.00815   0.00215   0.0000   0.6535   0.5117
  -2.000  -0.2283   0.00808   0.00211   0.0001   0.6490   0.5322
  -1.750  -0.2002   0.00804   0.00207   0.0002   0.6450   0.5503
  -1.500  -0.1720   0.00797   0.00206   0.0002   0.6405   0.5653
  -1.250  -0.1435   0.00792   0.00204   0.0002   0.6358   0.5757
  -1.000  -0.1150   0.00789   0.00202   0.0002   0.6308   0.5837
  -0.750  -0.0864   0.00788   0.00198   0.0002   0.6260   0.5905
  -0.500  -0.0576   0.00785   0.00199   0.0001   0.6206   0.5973
  -0.250  -0.0287   0.00784   0.00199   0.0000   0.6147   0.6037
   0.000   0.0000   0.00784   0.00197   0.0000   0.6090   0.6090
   0.250   0.0287   0.00784   0.00199   0.0000   0.6037   0.6147
   0.500   0.0576   0.00785   0.00199  -0.0001   0.5973   0.6206
   0.750   0.0864   0.00788   0.00198  -0.0002   0.5905   0.6260
   1.000   0.1150   0.00789   0.00202  -0.0002   0.5838   0.6308
   1.250   0.1435   0.00792   0.00204  -0.0002   0.5757   0.6358
   1.500   0.1720   0.00797   0.00206  -0.0002   0.5651   0.6406
   1.750   0.2002   0.00804   0.00207  -0.0002   0.5498   0.6450
   2.000   0.2283   0.00808   0.00211  -0.0001   0.5315   0.6490
   2.250   0.2563   0.00815   0.00215   0.0000   0.5109   0.6534
   2.500   0.2842   0.00825   0.00221   0.0001   0.4891   0.6584
   2.750   0.3112   0.00845   0.00227   0.0003   0.4515   0.6633
   3.000   0.3366   0.00880   0.00241   0.0006   0.3987   0.6677
   3.250   0.3609   0.00928   0.00265   0.0011   0.3334   0.6725
   3.500   0.3855   0.00976   0.00291   0.0014   0.2778   0.6776
   3.750   0.4092   0.01037   0.00322   0.0019   0.2138   0.6823
   4.000   0.4323   0.01099   0.00356   0.0024   0.1497   0.6861
   4.250   0.4562   0.01148   0.00388   0.0028   0.1075   0.6900
   4.500   0.4809   0.01190   0.00417   0.0032   0.0823   0.6943
   4.750   0.5060   0.01227   0.00445   0.0035   0.0605   0.6986
   5.000   0.5316   0.01259   0.00471   0.0038   0.0491   0.7024
   5.250   0.5562   0.01297   0.00502   0.0042   0.0332   0.7056
   5.500   0.5811   0.01329   0.00532   0.0046   0.0272   0.7089
   5.750   0.6065   0.01356   0.00561   0.0050   0.0220   0.7127
   6.000   0.6309   0.01392   0.00594   0.0054   0.0168   0.7167
   6.250   0.6556   0.01425   0.00626   0.0059   0.0156   0.7205
   6.500   0.6801   0.01457   0.00659   0.0063   0.0151   0.7237
   6.750   0.7041   0.01489   0.00695   0.0068   0.0146   0.7266
   7.000   0.7276   0.01525   0.00735   0.0074   0.0142   0.7297
   7.250   0.7505   0.01564   0.00777   0.0081   0.0139   0.7330
   7.500   0.7733   0.01603   0.00819   0.0087   0.0137   0.7365
   7.750   0.7952   0.01647   0.00866   0.0095   0.0135   0.7401
   8.000   0.8158   0.01695   0.00918   0.0104   0.0133   0.7432
   8.250   0.8361   0.01742   0.00970   0.0114   0.0132   0.7465
   8.500   0.8557   0.01790   0.01023   0.0125   0.0131   0.7500
   8.750   0.8743   0.01842   0.01079   0.0136   0.0130   0.7538
   9.000   0.8918   0.01896   0.01136   0.0149   0.0130   0.7574
   9.250   0.9064   0.01952   0.01197   0.0166   0.0129   0.7604
   9.500   0.9175   0.02009   0.01261   0.0188   0.0128   0.7638
   9.750   0.9279   0.02078   0.01336   0.0210   0.0127   0.7675
  10.000   0.9380   0.02157   0.01419   0.0228   0.0127   0.7714
  10.250   0.9474   0.02249   0.01517   0.0245   0.0126   0.7750
  10.500   0.9577   0.02340   0.01615   0.0258   0.0126   0.7785
  10.750   0.9672   0.02443   0.01726   0.0272   0.0125   0.7823
  11.000   0.9777   0.02544   0.01833   0.0283   0.0125   0.7863
  11.500   0.9965   0.02768   0.02071   0.0306   0.0123   0.7949
  11.750   1.0041   0.02897   0.02209   0.0317   0.0122   0.7997
  12.000   1.0132   0.03018   0.02338   0.0326   0.0121   0.8047
  12.250   1.0204   0.03158   0.02487   0.0335   0.0120   0.8110
  12.500   1.0269   0.03303   0.02643   0.0344   0.0120   0.8197
  12.750   1.0345   0.03438   0.02792   0.0352   0.0119   0.8338
  13.000   1.0479   0.03597   0.02979   0.0344   0.0119   0.8878
  13.250   1.0792   0.03837   0.03235   0.0289   0.0118   1.0000
  13.500   1.0856   0.04021   0.03426   0.0291   0.0118   1.0000
  13.750   1.0909   0.04221   0.03631   0.0292   0.0118   1.0000
  14.000   1.0952   0.04435   0.03852   0.0293   0.0117   1.0000
  14.250   1.0996   0.04652   0.04077   0.0292   0.0117   1.0000
  14.500   1.1031   0.04886   0.04317   0.0290   0.0117   1.0000
  14.750   1.1059   0.05132   0.04572   0.0286   0.0117   1.0000
  15.000   1.1086   0.05393   0.04841   0.0282   0.0117   1.0000
  15.250   1.1108   0.05668   0.05124   0.0275   0.0116   1.0000
  15.500   1.1119   0.05962   0.05427   0.0268   0.0117   1.0000
  15.750   1.1121   0.06276   0.05750   0.0258   0.0116   1.0000
  16.000   1.1118   0.06609   0.06092   0.0247   0.0116   1.0000
  16.250   1.1110   0.06956   0.06449   0.0234   0.0116   1.0000
  16.500   1.1087   0.07334   0.06837   0.0219   0.0115   1.0000
  16.750   1.1064   0.07722   0.07235   0.0202   0.0115   1.0000
  17.000   1.1021   0.08152   0.07675   0.0184   0.0115   1.0000
  17.250   1.0968   0.08609   0.08145   0.0162   0.0115   1.0000
  17.500   1.0911   0.09083   0.08630   0.0139   0.0115   1.0000
  17.750   1.0844   0.09591   0.09149   0.0113   0.0115   1.0000
  18.000   1.0762   0.10140   0.09711   0.0083   0.0115   1.0000
  18.250   1.0669   0.10721   0.10305   0.0051   0.0115   1.0000
  18.500   1.0569   0.11328   0.10924   0.0017   0.0115   1.0000
  18.750   1.0455   0.11986   0.11596  -0.0021   0.0115   1.0000
  19.000   1.0337   0.12661   0.12283  -0.0061   0.0115   1.0000
<< Back to FX 71-L-150/25 AIRFOIL (fx711525-il)

Polar data table (+)

Polar graphs


<< Back to FX 71-L-150/25 AIRFOIL (fx711525-il)