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

FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il)
Reynolds number: 100,000
Max Cl/Cd: 39.63 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxl142k-il-100000-n5.txt
Download as CSV file: xf-fxl142k-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.8461   0.12085   0.11556   0.0033   1.0000   0.0489
 -15.500  -0.9085   0.10277   0.09735  -0.0080   1.0000   0.0479
 -15.250  -0.9486   0.09134   0.08571  -0.0151   1.0000   0.0473
 -15.000  -0.9799   0.08270   0.07682  -0.0202   1.0000   0.0473
 -14.750  -1.0038   0.07588   0.06975  -0.0238   1.0000   0.0476
 -14.500  -1.0243   0.07007   0.06368  -0.0267   1.0000   0.0483
 -14.250  -1.0419   0.06502   0.05835  -0.0289   1.0000   0.0490
 -14.000  -1.0442   0.06188   0.05517  -0.0296   1.0000   0.0505
 -13.750  -1.0418   0.05959   0.05289  -0.0302   1.0000   0.0522
 -13.500  -1.0441   0.05675   0.04994  -0.0308   1.0000   0.0536
 -13.250  -1.0471   0.05381   0.04684  -0.0312   1.0000   0.0549
 -13.000  -1.0488   0.05099   0.04381  -0.0313   1.0000   0.0562
 -12.750  -1.0490   0.04835   0.04092  -0.0311   1.0000   0.0575
 -12.500  -1.0486   0.04596   0.03827  -0.0307   1.0000   0.0590
 -12.250  -1.0466   0.04384   0.03588  -0.0301   1.0000   0.0604
 -12.000  -1.0359   0.04188   0.03386  -0.0294   1.0000   0.0622
 -11.750  -1.0252   0.04026   0.03221  -0.0286   1.0000   0.0638
 -11.500  -1.0144   0.03872   0.03060  -0.0278   1.0000   0.0654
 -11.250  -1.0028   0.03724   0.02902  -0.0268   1.0000   0.0671
 -11.000  -0.9912   0.03585   0.02750  -0.0257   1.0000   0.0693
 -10.750  -0.9788   0.03454   0.02604  -0.0245   1.0000   0.0716
 -10.500  -0.9656   0.03336   0.02463  -0.0233   1.0000   0.0737
 -10.250  -0.9518   0.03203   0.02339  -0.0220   1.0000   0.0759
 -10.000  -0.9396   0.03093   0.02227  -0.0205   1.0000   0.0781
  -9.750  -0.9262   0.02988   0.02119  -0.0191   1.0000   0.0806
  -9.500  -0.9114   0.02890   0.02013  -0.0178   1.0000   0.0840
  -9.250  -0.8962   0.02791   0.01910  -0.0165   1.0000   0.0876
  -9.000  -0.8824   0.02692   0.01814  -0.0151   1.0000   0.0917
  -8.750  -0.8665   0.02602   0.01716  -0.0138   1.0000   0.0968
  -8.500  -0.8508   0.02508   0.01619  -0.0124   1.0000   0.1024
  -8.250  -0.8357   0.02414   0.01529  -0.0110   1.0000   0.1091
  -8.000  -0.8192   0.02329   0.01441  -0.0097   1.0000   0.1177
  -7.750  -0.8024   0.02244   0.01359  -0.0085   1.0000   0.1280
  -7.500  -0.7854   0.02162   0.01281  -0.0073   1.0000   0.1410
  -7.250  -0.7681   0.02080   0.01203  -0.0061   1.0000   0.1561
  -7.000  -0.7508   0.02000   0.01132  -0.0049   1.0000   0.1735
  -6.750  -0.7336   0.01920   0.01065  -0.0036   1.0000   0.1946
  -6.500  -0.7161   0.01844   0.01005  -0.0024   1.0000   0.2224
  -6.250  -0.6994   0.01771   0.00951  -0.0011   1.0000   0.2566
  -6.000  -0.6730   0.01698   0.00904  -0.0017   0.9747   0.3026
  -5.750  -0.6344   0.01648   0.00869  -0.0044   0.9358   0.3536
  -5.500  -0.5985   0.01622   0.00853  -0.0062   0.9012   0.3998
  -5.250  -0.5647   0.01618   0.00851  -0.0073   0.8752   0.4369
  -5.000  -0.5355   0.01627   0.00851  -0.0072   0.8519   0.4634
  -4.750  -0.5082   0.01631   0.00835  -0.0070   0.8327   0.4845
  -4.500  -0.4814   0.01632   0.00821  -0.0065   0.8162   0.4984
  -4.250  -0.4550   0.01632   0.00811  -0.0060   0.8002   0.5092
  -4.000  -0.4290   0.01632   0.00803  -0.0055   0.7836   0.5208
  -3.750  -0.4031   0.01639   0.00801  -0.0048   0.7707   0.5345
  -3.500  -0.3773   0.01648   0.00798  -0.0041   0.7603   0.5489
  -3.250  -0.3513   0.01654   0.00790  -0.0034   0.7511   0.5623
  -3.000  -0.3246   0.01660   0.00787  -0.0029   0.7425   0.5727
  -2.750  -0.2978   0.01660   0.00782  -0.0025   0.7334   0.5809
  -2.500  -0.2710   0.01661   0.00768  -0.0022   0.7256   0.5904
  -2.250  -0.2438   0.01662   0.00769  -0.0019   0.7167   0.5975
  -2.000  -0.2171   0.01659   0.00753  -0.0016   0.7095   0.6060
  -1.750  -0.1898   0.01655   0.00750  -0.0014   0.7014   0.6118
  -1.500  -0.1629   0.01652   0.00735  -0.0012   0.6951   0.6192
  -1.250  -0.1357   0.01646   0.00732  -0.0011   0.6873   0.6249
  -1.000  -0.1086   0.01643   0.00723  -0.0008   0.6811   0.6316
  -0.750  -0.0815   0.01639   0.00719  -0.0007   0.6743   0.6379
  -0.500  -0.0543   0.01637   0.00718  -0.0004   0.6680   0.6440
  -0.250  -0.0272   0.01636   0.00713  -0.0002   0.6625   0.6506
   0.000   0.0000   0.01636   0.00717   0.0000   0.6559   0.6560
   0.250   0.0272   0.01636   0.00713   0.0002   0.6506   0.6625
   0.500   0.0543   0.01637   0.00718   0.0004   0.6440   0.6680
   0.750   0.0815   0.01639   0.00719   0.0007   0.6379   0.6742
   1.000   0.1086   0.01643   0.00723   0.0008   0.6316   0.6811
   1.250   0.1357   0.01646   0.00732   0.0011   0.6249   0.6873
   1.500   0.1629   0.01652   0.00735   0.0012   0.6193   0.6951
   1.750   0.1898   0.01655   0.00750   0.0014   0.6118   0.7014
   2.000   0.2171   0.01659   0.00754   0.0017   0.6060   0.7095
   2.250   0.2438   0.01662   0.00769   0.0019   0.5975   0.7168
   2.500   0.2710   0.01661   0.00768   0.0022   0.5903   0.7257
   2.750   0.2978   0.01660   0.00782   0.0025   0.5810   0.7334
   3.000   0.3246   0.01659   0.00787   0.0029   0.5726   0.7425
   3.250   0.3513   0.01654   0.00789   0.0035   0.5623   0.7512
   3.500   0.3773   0.01648   0.00797   0.0041   0.5487   0.7603
   3.750   0.4031   0.01639   0.00800   0.0048   0.5344   0.7707
   4.000   0.4290   0.01632   0.00803   0.0055   0.5207   0.7836
   4.250   0.4550   0.01632   0.00811   0.0060   0.5092   0.8002
   4.500   0.4814   0.01632   0.00821   0.0065   0.4983   0.8163
   4.750   0.5082   0.01631   0.00835   0.0070   0.4845   0.8327
   5.000   0.5356   0.01628   0.00852   0.0072   0.4641   0.8518
   5.250   0.5647   0.01618   0.00851   0.0072   0.4374   0.8751
   5.500   0.5986   0.01622   0.00853   0.0062   0.4001   0.9011
   5.750   0.6343   0.01648   0.00869   0.0045   0.3531   0.9357
   6.000   0.6729   0.01698   0.00902   0.0017   0.3023   0.9747
   6.250   0.6994   0.01771   0.00951   0.0011   0.2566   1.0000
   6.500   0.7161   0.01844   0.01005   0.0024   0.2223   1.0000
   6.750   0.7336   0.01920   0.01065   0.0037   0.1946   1.0000
   7.000   0.7508   0.02000   0.01131   0.0049   0.1736   1.0000
   7.250   0.7682   0.02080   0.01203   0.0061   0.1561   1.0000
   7.500   0.7854   0.02162   0.01281   0.0073   0.1408   1.0000
   7.750   0.8025   0.02245   0.01359   0.0085   0.1277   1.0000
   8.000   0.8192   0.02329   0.01441   0.0097   0.1176   1.0000
   8.250   0.8358   0.02414   0.01529   0.0110   0.1091   1.0000
   8.500   0.8509   0.02508   0.01620   0.0124   0.1024   1.0000
   8.750   0.8666   0.02602   0.01716   0.0138   0.0967   1.0000
   9.000   0.8825   0.02692   0.01813   0.0151   0.0915   1.0000
   9.250   0.8964   0.02791   0.01910   0.0165   0.0875   1.0000
   9.500   0.9115   0.02889   0.02013   0.0178   0.0839   1.0000
   9.750   0.9263   0.02988   0.02119   0.0191   0.0805   1.0000
  10.000   0.9399   0.03092   0.02227   0.0205   0.0781   1.0000
  10.250   0.9520   0.03204   0.02339   0.0220   0.0758   1.0000
  10.500   0.9656   0.03334   0.02462   0.0233   0.0736   1.0000
  10.750   0.9790   0.03454   0.02604   0.0245   0.0715   1.0000
  11.000   0.9913   0.03585   0.02750   0.0257   0.0692   1.0000
  11.250   1.0030   0.03723   0.02900   0.0267   0.0670   1.0000
  11.500   1.0147   0.03871   0.03059   0.0277   0.0653   1.0000
  11.750   1.0257   0.04026   0.03221   0.0286   0.0638   1.0000
  12.000   1.0364   0.04188   0.03385   0.0293   0.0620   1.0000
  12.250   1.0470   0.04386   0.03590   0.0300   0.0603   1.0000
  12.500   1.0491   0.04597   0.03828   0.0306   0.0590   1.0000
  12.750   1.0498   0.04835   0.04092   0.0310   0.0575   1.0000
  13.000   1.0494   0.05101   0.04383   0.0312   0.0561   1.0000
  13.250   1.0475   0.05380   0.04682   0.0310   0.0548   1.0000
  13.500   1.0448   0.05671   0.04989   0.0306   0.0534   1.0000
  13.750   1.0430   0.05951   0.05280   0.0301   0.0521   1.0000
  14.000   1.0457   0.06180   0.05508   0.0296   0.0504   1.0000
  14.250   1.0428   0.06504   0.05836   0.0288   0.0490   1.0000
  14.500   1.0254   0.07007   0.06369   0.0266   0.0483   1.0000
  14.750   1.0046   0.07594   0.06982   0.0237   0.0477   1.0000
  15.000   0.9800   0.08281   0.07694   0.0199   0.0472   1.0000
  15.250   0.9490   0.09148   0.08584   0.0148   0.0472   1.0000
  15.500   0.9091   0.10290   0.09748   0.0078   0.0479   1.0000
  15.750   0.8443   0.12165   0.11637  -0.0039   0.0489   1.0000
<< Back to FX LIII-142 K 25 AIRFOIL (fxl142k-il)

Polar data table (+)

Polar graphs


<< Back to FX LIII-142 K 25 AIRFOIL (fxl142k-il)