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FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il)
Reynolds number: 100,000
Max Cl/Cd: 42.13 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxl142k-il-100000.txt
Download as CSV file: xf-fxl142k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX LIII-142 K 25 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8092   0.10269   0.09752  -0.0118   1.0000   0.1005
 -13.250  -0.8315   0.09341   0.08822  -0.0160   1.0000   0.0995
 -13.000  -0.8703   0.08324   0.07801  -0.0217   1.0000   0.0979
 -12.750  -0.9162   0.07405   0.06868  -0.0268   1.0000   0.0963
 -12.500  -0.9576   0.06694   0.06138  -0.0298   1.0000   0.0951
 -12.250  -0.9913   0.06169   0.05591  -0.0307   1.0000   0.0945
 -12.000  -1.0177   0.05769   0.05168  -0.0295   1.0000   0.0944
 -11.750  -1.0370   0.05442   0.04815  -0.0270   1.0000   0.0948
 -11.500  -1.0472   0.05120   0.04463  -0.0250   1.0000   0.0956
 -11.250  -1.0519   0.04830   0.04139  -0.0229   1.0000   0.0971
 -11.000  -1.0536   0.04580   0.03847  -0.0207   1.0000   0.0990
 -10.750  -1.0516   0.04360   0.03583  -0.0185   1.0000   0.1008
 -10.500  -1.0328   0.04043   0.03264  -0.0184   1.0000   0.1036
 -10.250  -1.0157   0.03842   0.03047  -0.0175   1.0000   0.1061
 -10.000  -0.9985   0.03658   0.02844  -0.0166   1.0000   0.1091
  -9.750  -0.9823   0.03494   0.02652  -0.0154   1.0000   0.1128
  -9.500  -0.9649   0.03321   0.02448  -0.0142   1.0000   0.1162
  -9.250  -0.9397   0.03135   0.02274  -0.0142   1.0000   0.1203
  -9.000  -0.9173   0.02993   0.02123  -0.0135   1.0000   0.1248
  -8.750  -0.8971   0.02874   0.01977  -0.0125   1.0000   0.1301
  -8.500  -0.8724   0.02713   0.01837  -0.0123   1.0000   0.1372
  -8.250  -0.8515   0.02601   0.01705  -0.0113   1.0000   0.1452
  -8.000  -0.8288   0.02446   0.01577  -0.0106   1.0000   0.1558
  -7.750  -0.8095   0.02309   0.01455  -0.0095   1.0000   0.1699
  -7.500  -0.7925   0.02180   0.01341  -0.0080   1.0000   0.1901
  -7.250  -0.7779   0.02056   0.01245  -0.0063   1.0000   0.2157
  -7.000  -0.7636   0.01939   0.01155  -0.0046   1.0000   0.2498
  -6.750  -0.7504   0.01829   0.01085  -0.0026   1.0000   0.2926
  -6.500  -0.7364   0.01748   0.01043  -0.0005   1.0000   0.3482
  -6.250  -0.7205   0.01713   0.01035   0.0016   1.0000   0.4002
  -6.000  -0.7033   0.01714   0.01049   0.0036   1.0000   0.4394
  -5.750  -0.6879   0.01737   0.01078   0.0058   1.0000   0.4658
  -5.500  -0.6860   0.01753   0.01088   0.0093   1.0000   0.4855
  -5.250  -0.6518   0.01808   0.01146   0.0076   0.9881   0.5099
  -5.000  -0.6003   0.01888   0.01225   0.0035   0.9734   0.5363
  -4.750  -0.5512   0.01940   0.01264  -0.0002   0.9595   0.5610
  -4.500  -0.5040   0.01975   0.01297  -0.0034   0.9457   0.5772
  -4.250  -0.4595   0.01982   0.01292  -0.0063   0.9326   0.5911
  -4.000  -0.4194   0.02002   0.01310  -0.0079   0.9181   0.6026
  -3.750  -0.3853   0.02021   0.01324  -0.0085   0.9032   0.6158
  -3.500  -0.3542   0.02045   0.01343  -0.0083   0.8896   0.6297
  -3.250  -0.3248   0.02067   0.01361  -0.0077   0.8769   0.6427
  -3.000  -0.2976   0.02075   0.01363  -0.0071   0.8647   0.6543
  -2.750  -0.2722   0.02065   0.01342  -0.0066   0.8536   0.6654
  -2.500  -0.2459   0.02070   0.01344  -0.0058   0.8422   0.6730
  -2.250  -0.2221   0.02055   0.01322  -0.0052   0.8320   0.6825
  -1.750  -0.1725   0.02047   0.01305  -0.0037   0.8136   0.7007
  -1.500  -0.1495   0.02031   0.01280  -0.0033   0.8049   0.7108
  -1.250  -0.1235   0.02025   0.01274  -0.0026   0.7967   0.7172
  -1.000  -0.1003   0.02010   0.01253  -0.0023   0.7879   0.7265
  -0.750  -0.0745   0.02004   0.01248  -0.0017   0.7804   0.7333
  -0.500  -0.0504   0.01990   0.01230  -0.0013   0.7723   0.7421
  -0.250  -0.0249   0.01990   0.01232  -0.0006   0.7647   0.7491
   0.000   0.0000   0.01982   0.01221   0.0000   0.7574   0.7574
   0.250   0.0249   0.01990   0.01232   0.0006   0.7491   0.7647
   0.500   0.0504   0.01990   0.01230   0.0013   0.7420   0.7723
   0.750   0.0745   0.02004   0.01248   0.0017   0.7332   0.7805
   1.000   0.1003   0.02010   0.01253   0.0023   0.7265   0.7879
   1.250   0.1235   0.02025   0.01274   0.0026   0.7172   0.7967
   1.500   0.1496   0.02031   0.01280   0.0033   0.7108   0.8048
   1.750   0.1725   0.02047   0.01304   0.0037   0.7006   0.8137
   2.000   0.1966   0.02052   0.01311   0.0044   0.6919   0.8236
   2.250   0.2221   0.02055   0.01322   0.0052   0.6825   0.8321
   2.500   0.2459   0.02070   0.01344   0.0058   0.6730   0.8422
   2.750   0.2722   0.02066   0.01342   0.0066   0.6654   0.8536
   3.000   0.2976   0.02075   0.01363   0.0071   0.6543   0.8648
   3.250   0.3248   0.02067   0.01361   0.0077   0.6427   0.8769
   3.500   0.3542   0.02044   0.01341   0.0083   0.6295   0.8896
   3.750   0.3853   0.02022   0.01324   0.0085   0.6158   0.9032
   4.000   0.4194   0.02002   0.01309   0.0080   0.6026   0.9181
   4.250   0.4595   0.01982   0.01292   0.0063   0.5911   0.9326
   4.500   0.5040   0.01975   0.01297   0.0034   0.5772   0.9458
   4.750   0.5512   0.01941   0.01265   0.0002   0.5611   0.9596
   5.000   0.6002   0.01891   0.01229  -0.0036   0.5367   0.9735
   5.250   0.6517   0.01808   0.01146  -0.0076   0.5099   0.9881
   5.500   0.6859   0.01753   0.01088  -0.0093   0.4855   1.0000
   5.750   0.6879   0.01737   0.01078  -0.0058   0.4657   1.0000
   6.000   0.7032   0.01714   0.01049  -0.0036   0.4394   1.0000
   6.250   0.7205   0.01713   0.01035  -0.0016   0.4001   1.0000
   6.500   0.7364   0.01748   0.01043   0.0005   0.3481   1.0000
   6.750   0.7504   0.01829   0.01085   0.0026   0.2926   1.0000
   7.000   0.7636   0.01939   0.01155   0.0046   0.2499   1.0000
   7.250   0.7779   0.02055   0.01245   0.0063   0.2158   1.0000
   7.500   0.7926   0.02180   0.01341   0.0080   0.1900   1.0000
   7.750   0.8095   0.02309   0.01455   0.0095   0.1696   1.0000
   8.000   0.8289   0.02446   0.01577   0.0106   0.1558   1.0000
   8.250   0.8515   0.02601   0.01705   0.0112   0.1452   1.0000
   8.500   0.8724   0.02713   0.01836   0.0123   0.1371   1.0000
   8.750   0.8970   0.02873   0.01976   0.0125   0.1300   1.0000
   9.000   0.9173   0.02993   0.02123   0.0135   0.1247   1.0000
   9.250   0.9398   0.03135   0.02274   0.0142   0.1203   1.0000
   9.500   0.9651   0.03327   0.02452   0.0142   0.1160   1.0000
   9.750   0.9821   0.03494   0.02651   0.0154   0.1127   1.0000
  10.000   0.9985   0.03657   0.02842   0.0166   0.1090   1.0000
  10.250   1.0158   0.03842   0.03046   0.0175   0.1060   1.0000
  10.500   1.0330   0.04042   0.03263   0.0183   0.1035   1.0000
  10.750   1.0517   0.04366   0.03589   0.0185   0.1008   1.0000
  11.000   1.0538   0.04586   0.03854   0.0207   0.0991   1.0000
  11.250   1.0520   0.04835   0.04144   0.0229   0.0971   1.0000
  11.500   1.0472   0.05122   0.04465   0.0250   0.0956   1.0000
  11.750   1.0370   0.05447   0.04821   0.0270   0.0948   1.0000
  12.000   1.0180   0.05767   0.05166   0.0295   0.0942   1.0000
  12.250   0.9916   0.06171   0.05593   0.0306   0.0944   1.0000
  12.500   0.9578   0.06699   0.06143   0.0297   0.0951   1.0000
  12.750   0.9163   0.07413   0.06877   0.0267   0.0963   1.0000
  13.000   0.8699   0.08344   0.07822   0.0215   0.0980   1.0000
  13.250   0.8301   0.09385   0.08865   0.0156   0.0995   1.0000
  13.500   0.8088   0.10302   0.09785   0.0115   0.1005   1.0000
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