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FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il)
Reynolds number: 100,000
Max Cl/Cd: 36.7 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx711520-il-100000.txt
Download as CSV file: xf-fx711520-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7219   0.11267   0.10742  -0.0054   1.0000   0.0699
 -13.000  -0.8443   0.08761   0.08196  -0.0232   1.0000   0.0630
 -12.750  -0.8437   0.08321   0.07753  -0.0244   1.0000   0.0623
 -12.500  -0.8648   0.07732   0.07151  -0.0270   1.0000   0.0614
 -12.250  -0.8926   0.07148   0.06548  -0.0291   1.0000   0.0605
 -12.000  -0.9242   0.06609   0.05983  -0.0303   1.0000   0.0595
 -11.750  -0.9673   0.06103   0.05435  -0.0299   1.0000   0.0582
 -11.500  -1.0070   0.05785   0.05065  -0.0266   1.0000   0.0571
 -11.250  -1.0010   0.05464   0.04728  -0.0259   1.0000   0.0567
 -11.000  -0.9968   0.05147   0.04389  -0.0249   1.0000   0.0564
 -10.750  -0.9904   0.04853   0.04069  -0.0239   1.0000   0.0561
 -10.500  -0.9801   0.04566   0.03754  -0.0230   1.0000   0.0559
 -10.250  -0.9661   0.04298   0.03458  -0.0223   1.0000   0.0559
 -10.000  -0.9486   0.04051   0.03185  -0.0217   1.0000   0.0561
  -9.750  -0.9279   0.03821   0.02928  -0.0214   1.0000   0.0566
  -9.500  -0.9041   0.03614   0.02697  -0.0212   1.0000   0.0573
  -9.250  -0.8719   0.03417   0.02513  -0.0220   1.0000   0.0587
  -9.000  -0.8438   0.03260   0.02357  -0.0224   1.0000   0.0610
  -8.750  -0.8166   0.03109   0.02201  -0.0225   1.0000   0.0638
  -8.500  -0.7907   0.02981   0.02086  -0.0228   1.0000   0.0675
  -8.250  -0.7664   0.02848   0.01964  -0.0227   1.0000   0.0721
  -8.000  -0.7465   0.02717   0.01844  -0.0222   1.0000   0.0787
  -7.750  -0.7346   0.02584   0.01729  -0.0210   1.0000   0.0876
  -7.500  -0.7377   0.02487   0.01648  -0.0177   1.0000   0.0970
  -7.250  -0.7215   0.02297   0.01489  -0.0184   0.9816   0.1290
  -7.000  -0.6997   0.02053   0.01312  -0.0207   0.9666   0.2038
  -6.750  -0.6808   0.01856   0.01193  -0.0219   0.9538   0.3202
  -6.500  -0.6570   0.01796   0.01185  -0.0220   0.9434   0.4203
  -6.250  -0.6241   0.01829   0.01232  -0.0226   0.9355   0.4848
  -6.000  -0.5971   0.01900   0.01297  -0.0218   0.9257   0.5252
  -5.750  -0.5616   0.02042   0.01439  -0.0213   0.9186   0.5524
  -5.500  -0.5299   0.02194   0.01588  -0.0200   0.9111   0.5727
  -5.250  -0.4980   0.02338   0.01724  -0.0186   0.9038   0.5900
  -5.000  -0.4691   0.02430   0.01803  -0.0176   0.8972   0.6064
  -4.750  -0.4330   0.02580   0.01953  -0.0163   0.8911   0.6144
  -4.500  -0.4084   0.02621   0.01981  -0.0153   0.8846   0.6284
  -4.250  -0.3730   0.02738   0.02092  -0.0140   0.8795   0.6362
  -4.000  -0.3521   0.02753   0.02099  -0.0130   0.8726   0.6493
  -3.750  -0.3198   0.02836   0.02176  -0.0118   0.8666   0.6572
  -3.500  -0.3013   0.02821   0.02150  -0.0107   0.8609   0.6697
  -3.250  -0.2706   0.02871   0.02197  -0.0100   0.8559   0.6763
  -3.000  -0.2566   0.02833   0.02150  -0.0092   0.8490   0.6892
  -2.750  -0.2261   0.02870   0.02183  -0.0081   0.8433   0.6946
  -2.500  -0.2084   0.02859   0.02165  -0.0072   0.8368   0.7053
  -2.250  -0.1857   0.02851   0.02154  -0.0065   0.8303   0.7123
  -2.000  -0.1602   0.02860   0.02158  -0.0056   0.8250   0.7192
  -1.750  -0.1464   0.02834   0.02126  -0.0048   0.8188   0.7297
  -1.500  -0.1202   0.02845   0.02137  -0.0041   0.8125   0.7352
  -1.250  -0.0996   0.02838   0.02126  -0.0033   0.8072   0.7434
  -1.000  -0.0813   0.02825   0.02109  -0.0027   0.8021   0.7508
  -0.750  -0.0591   0.02828   0.02115  -0.0023   0.7958   0.7560
  -0.500  -0.0392   0.02821   0.02105  -0.0017   0.7901   0.7634
  -0.250  -0.0197   0.02818   0.02100  -0.0008   0.7846   0.7706
   0.000   0.0000   0.02829   0.02114   0.0000   0.7769   0.7769
   0.250   0.0197   0.02818   0.02100   0.0008   0.7706   0.7846
   0.500   0.0392   0.02821   0.02105   0.0017   0.7634   0.7901
   0.750   0.0591   0.02829   0.02115   0.0023   0.7560   0.7958
   1.000   0.0814   0.02825   0.02109   0.0027   0.7508   0.8021
   1.250   0.0996   0.02839   0.02127   0.0033   0.7435   0.8073
   1.500   0.1201   0.02845   0.02138   0.0041   0.7352   0.8125
   1.750   0.1464   0.02834   0.02126   0.0048   0.7298   0.8188
   2.000   0.1602   0.02860   0.02158   0.0056   0.7192   0.8250
   2.250   0.1857   0.02851   0.02154   0.0065   0.7123   0.8303
   2.500   0.2083   0.02859   0.02165   0.0072   0.7052   0.8367
   2.750   0.2263   0.02869   0.02181   0.0081   0.6946   0.8432
   3.000   0.2566   0.02833   0.02151   0.0092   0.6892   0.8490
   3.250   0.2705   0.02872   0.02198   0.0100   0.6763   0.8559
   3.500   0.3012   0.02823   0.02152   0.0107   0.6697   0.8610
   3.750   0.3198   0.02835   0.02176   0.0118   0.6572   0.8667
   4.000   0.3519   0.02756   0.02102   0.0130   0.6494   0.8727
   4.250   0.3731   0.02738   0.02092   0.0141   0.6362   0.8796
   4.500   0.4084   0.02621   0.01981   0.0153   0.6284   0.8846
   4.750   0.4330   0.02581   0.01953   0.0163   0.6144   0.8911
   5.000   0.4691   0.02430   0.01804   0.0176   0.6064   0.8972
   5.250   0.4979   0.02340   0.01726   0.0186   0.5901   0.9037
   5.500   0.5299   0.02195   0.01588   0.0200   0.5728   0.9111
   5.750   0.5617   0.02042   0.01438   0.0213   0.5524   0.9186
   6.000   0.5971   0.01900   0.01297   0.0218   0.5250   0.9258
   6.250   0.6241   0.01828   0.01232   0.0226   0.4842   0.9355
   6.500   0.6570   0.01796   0.01184   0.0220   0.4199   0.9434
   6.750   0.6808   0.01855   0.01193   0.0219   0.3201   0.9538
   7.000   0.6996   0.02054   0.01312   0.0207   0.2032   0.9666
   7.250   0.7215   0.02297   0.01489   0.0184   0.1289   0.9816
   7.500   0.7372   0.02488   0.01648   0.0177   0.0965   1.0000
   7.750   0.7342   0.02587   0.01731   0.0210   0.0870   1.0000
   8.000   0.7467   0.02716   0.01844   0.0222   0.0786   1.0000
   8.250   0.7667   0.02848   0.01964   0.0227   0.0722   1.0000
   8.500   0.7912   0.02983   0.02088   0.0227   0.0674   1.0000
   8.750   0.8172   0.03112   0.02203   0.0225   0.0639   1.0000
   9.000   0.8438   0.03261   0.02358   0.0224   0.0608   1.0000
   9.250   0.8722   0.03418   0.02514   0.0220   0.0587   1.0000
   9.500   0.9045   0.03616   0.02698   0.0212   0.0573   1.0000
   9.750   0.9282   0.03822   0.02928   0.0214   0.0566   1.0000
  10.000   0.9487   0.04053   0.03188   0.0217   0.0561   1.0000
  10.250   0.9665   0.04299   0.03459   0.0222   0.0559   1.0000
  10.500   0.9804   0.04569   0.03756   0.0230   0.0559   1.0000
  10.750   0.9910   0.04852   0.04067   0.0238   0.0561   1.0000
  11.000   0.9975   0.05149   0.04390   0.0248   0.0564   1.0000
  11.250   1.0016   0.05463   0.04728   0.0258   0.0567   1.0000
  11.500   1.0077   0.05786   0.05066   0.0265   0.0571   1.0000
  11.750   0.9660   0.06113   0.05446   0.0299   0.0583   1.0000
  12.000   0.9237   0.06620   0.05995   0.0302   0.0596   1.0000
  12.250   0.8918   0.07165   0.06565   0.0290   0.0605   1.0000
  12.500   0.8657   0.07734   0.07154   0.0269   0.0615   1.0000
  12.750   0.8460   0.08311   0.07743   0.0244   0.0623   1.0000
  13.000   0.8478   0.08741   0.08174   0.0233   0.0631   1.0000
  13.250   0.5110   0.14493   0.14032  -0.0107   0.1380   1.0000
  13.500   0.5057   0.14908   0.14444  -0.0131   0.1365   1.0000
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