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FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il)
Reynolds number: 50,000
Max Cl/Cd: 28.29 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxl142k-il-50000-n5.txt
Download as CSV file: xf-fxl142k-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8241   0.09679   0.08924  -0.0134   1.0000   0.0866
 -13.250  -0.8672   0.08607   0.07838  -0.0200   1.0000   0.0862
 -13.000  -0.9012   0.07800   0.07013  -0.0244   1.0000   0.0861
 -12.750  -0.9308   0.07145   0.06334  -0.0275   1.0000   0.0863
 -12.500  -0.9558   0.06608   0.05769  -0.0293   1.0000   0.0868
 -12.250  -0.9418   0.06427   0.05597  -0.0289   1.0000   0.0895
 -12.000  -0.9456   0.06117   0.05274  -0.0291   1.0000   0.0914
 -11.750  -0.9518   0.05791   0.04929  -0.0291   1.0000   0.0931
 -11.500  -0.9564   0.05483   0.04598  -0.0285   1.0000   0.0949
 -11.250  -0.9577   0.05198   0.04285  -0.0276   1.0000   0.0967
 -11.000  -0.9570   0.04937   0.03992  -0.0263   1.0000   0.0989
 -10.750  -0.9486   0.04723   0.03757  -0.0252   1.0000   0.1020
 -10.500  -0.9321   0.04564   0.03599  -0.0245   1.0000   0.1059
 -10.250  -0.9187   0.04383   0.03402  -0.0236   1.0000   0.1101
 -10.000  -0.9028   0.04193   0.03182  -0.0227   1.0000   0.1143
  -9.750  -0.8795   0.04038   0.03027  -0.0222   1.0000   0.1187
  -9.500  -0.8596   0.03896   0.02880  -0.0215   1.0000   0.1243
  -9.250  -0.8418   0.03752   0.02717  -0.0205   1.0000   0.1314
  -9.000  -0.8268   0.03618   0.02589  -0.0195   1.0000   0.1397
  -8.750  -0.8122   0.03480   0.02449  -0.0183   1.0000   0.1494
  -8.500  -0.7981   0.03344   0.02309  -0.0170   1.0000   0.1610
  -8.250  -0.7858   0.03208   0.02185  -0.0155   1.0000   0.1724
  -8.000  -0.7742   0.03074   0.02062  -0.0140   1.0000   0.1861
  -7.750  -0.7626   0.02946   0.01944  -0.0125   1.0000   0.2025
  -7.500  -0.7516   0.02821   0.01831  -0.0109   1.0000   0.2249
  -7.250  -0.7405   0.02702   0.01732  -0.0092   1.0000   0.2542
  -7.000  -0.7288   0.02601   0.01663  -0.0074   1.0000   0.2885
  -6.750  -0.7151   0.02528   0.01617  -0.0055   1.0000   0.3302
  -6.500  -0.6994   0.02491   0.01602  -0.0035   1.0000   0.3717
  -6.250  -0.6824   0.02477   0.01599  -0.0016   1.0000   0.4102
  -6.000  -0.6637   0.02482   0.01606   0.0003   1.0000   0.4401
  -5.750  -0.6441   0.02496   0.01620   0.0021   1.0000   0.4628
  -5.500  -0.6280   0.02475   0.01589   0.0038   1.0000   0.4841
  -5.250  -0.6134   0.02459   0.01567   0.0058   1.0000   0.5019
  -5.000  -0.6010   0.02461   0.01568   0.0081   1.0000   0.5169
  -4.750  -0.5639   0.02490   0.01588   0.0064   0.9762   0.5347
  -4.500  -0.5225   0.02514   0.01599   0.0040   0.9549   0.5541
  -4.250  -0.4829   0.02529   0.01599   0.0019   0.9363   0.5748
  -4.000  -0.4445   0.02549   0.01608   0.0003   0.9190   0.5919
  -3.750  -0.4092   0.02546   0.01590  -0.0010   0.9018   0.6061
  -3.500  -0.3728   0.02540   0.01571  -0.0023   0.8872   0.6161
  -3.250  -0.3403   0.02524   0.01541  -0.0031   0.8728   0.6263
  -3.000  -0.3117   0.02506   0.01509  -0.0033   0.8584   0.6373
  -2.750  -0.2831   0.02497   0.01490  -0.0033   0.8452   0.6466
  -2.500  -0.2550   0.02486   0.01467  -0.0032   0.8332   0.6548
  -2.250  -0.2294   0.02464   0.01431  -0.0031   0.8221   0.6643
  -2.000  -0.2020   0.02459   0.01420  -0.0027   0.8110   0.6711
  -1.750  -0.1789   0.02441   0.01392  -0.0023   0.7993   0.6806
  -1.500  -0.1532   0.02435   0.01383  -0.0019   0.7885   0.6879
  -1.250  -0.1292   0.02419   0.01359  -0.0015   0.7785   0.6971
  -1.000  -0.1027   0.02409   0.01343  -0.0011   0.7699   0.7049
  -0.750  -0.0778   0.02397   0.01327  -0.0009   0.7610   0.7135
  -0.500  -0.0510   0.02387   0.01312  -0.0006   0.7536   0.7213
  -0.250  -0.0256   0.02382   0.01305  -0.0003   0.7450   0.7293
   0.000   0.0000   0.02380   0.01301   0.0000   0.7375   0.7374
   0.250   0.0256   0.02382   0.01305   0.0003   0.7293   0.7450
   0.500   0.0510   0.02387   0.01313   0.0006   0.7213   0.7536
   0.750   0.0778   0.02397   0.01327   0.0009   0.7134   0.7610
   1.000   0.1027   0.02409   0.01344   0.0011   0.7049   0.7699
   1.250   0.1292   0.02419   0.01360   0.0015   0.6971   0.7785
   1.500   0.1532   0.02435   0.01383   0.0019   0.6879   0.7885
   1.750   0.1789   0.02441   0.01392   0.0023   0.6805   0.7994
   2.000   0.2020   0.02459   0.01420   0.0027   0.6711   0.8110
   2.250   0.2293   0.02464   0.01431   0.0031   0.6642   0.8221
   2.500   0.2550   0.02486   0.01467   0.0032   0.6548   0.8332
   2.750   0.2831   0.02497   0.01489   0.0033   0.6465   0.8452
   3.000   0.3118   0.02505   0.01508   0.0033   0.6372   0.8584
   3.250   0.3403   0.02524   0.01541   0.0031   0.6263   0.8728
   3.500   0.3728   0.02540   0.01572   0.0023   0.6161   0.8872
   3.750   0.4092   0.02546   0.01590   0.0010   0.6061   0.9018
   4.000   0.4445   0.02549   0.01608  -0.0003   0.5919   0.9190
   4.250   0.4829   0.02529   0.01598  -0.0019   0.5750   0.9362
   4.500   0.5225   0.02513   0.01599  -0.0040   0.5540   0.9549
   4.750   0.5639   0.02489   0.01587  -0.0064   0.5346   0.9762
   5.000   0.6010   0.02460   0.01568  -0.0081   0.5168   1.0000
   5.250   0.6134   0.02459   0.01567  -0.0057   0.5019   1.0000
   5.500   0.6280   0.02475   0.01589  -0.0038   0.4840   1.0000
   5.750   0.6441   0.02496   0.01620  -0.0021   0.4629   1.0000
   6.000   0.6638   0.02482   0.01605  -0.0003   0.4403   1.0000
   6.250   0.6824   0.02477   0.01600   0.0016   0.4103   1.0000
   6.500   0.6994   0.02491   0.01602   0.0035   0.3717   1.0000
   6.750   0.7151   0.02528   0.01616   0.0055   0.3298   1.0000
   7.000   0.7288   0.02600   0.01663   0.0074   0.2885   1.0000
   7.250   0.7406   0.02701   0.01732   0.0092   0.2545   1.0000
   7.500   0.7516   0.02821   0.01831   0.0109   0.2249   1.0000
   7.750   0.7626   0.02946   0.01944   0.0125   0.2023   1.0000
   8.000   0.7743   0.03074   0.02062   0.0140   0.1859   1.0000
   8.250   0.7859   0.03208   0.02185   0.0155   0.1724   1.0000
   8.500   0.7983   0.03344   0.02309   0.0170   0.1610   1.0000
   8.750   0.8123   0.03480   0.02449   0.0182   0.1493   1.0000
   9.000   0.8270   0.03618   0.02589   0.0194   0.1397   1.0000
   9.250   0.8419   0.03752   0.02716   0.0205   0.1313   1.0000
   9.500   0.8599   0.03896   0.02880   0.0214   0.1242   1.0000
   9.750   0.8799   0.04038   0.03027   0.0222   0.1187   1.0000
  10.000   0.9032   0.04194   0.03182   0.0227   0.1143   1.0000
  10.250   0.9188   0.04384   0.03402   0.0236   0.1099   1.0000
  10.500   0.9322   0.04564   0.03599   0.0245   0.1058   1.0000
  10.750   0.9489   0.04720   0.03751   0.0251   0.1018   1.0000
  11.000   0.9570   0.04938   0.03989   0.0263   0.0988   1.0000
  11.250   0.9579   0.05199   0.04286   0.0275   0.0966   1.0000
  11.500   0.9566   0.05484   0.04599   0.0285   0.0948   1.0000
  11.750   0.9523   0.05792   0.04930   0.0290   0.0930   1.0000
  12.000   0.9464   0.06114   0.05271   0.0291   0.0913   1.0000
  12.250   0.9434   0.06419   0.05588   0.0289   0.0893   1.0000
  12.500   0.9563   0.06613   0.05774   0.0292   0.0868   1.0000
  12.750   0.9305   0.07153   0.06342   0.0273   0.0862   1.0000
  13.000   0.9004   0.07820   0.07033   0.0242   0.0860   1.0000
  13.250   0.8648   0.08651   0.07882   0.0195   0.0861   1.0000
  13.500   0.8218   0.09738   0.08982   0.0129   0.0865   1.0000
  13.750   0.7750   0.11107   0.10354   0.0044   0.0868   1.0000
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