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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 100,000
Max Cl/Cd: 39.69 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74080-il-100000.txt
Download as CSV file: xf-fx74080-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 74-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4322   0.10600   0.10197  -0.0211   1.0000   0.0459
  -7.000  -0.4425   0.10452   0.10055  -0.0193   1.0000   0.0460
  -6.750  -0.4555   0.10316   0.09924  -0.0175   1.0000   0.0465
  -6.500  -0.4645   0.10143   0.09758  -0.0182   1.0000   0.0477
  -6.250  -0.4682   0.09919   0.09537  -0.0199   1.0000   0.0482
  -6.000  -0.4662   0.09718   0.09335  -0.0261   1.0000   0.0491
  -5.750  -0.4413   0.09350   0.08952  -0.0365   0.9970   0.0495
  -5.500  -0.4462   0.08745   0.08355  -0.0283   0.9956   0.0521
  -5.250  -0.4309   0.08362   0.07970  -0.0309   0.9920   0.0583
  -5.000  -0.3950   0.07941   0.07529  -0.0431   0.9875   0.0621
  -4.750  -0.3794   0.07414   0.06998  -0.0466   0.9838   0.0646
  -4.500  -0.3646   0.07049   0.06633  -0.0470   0.9804   0.0686
  -4.250  -0.3150   0.06566   0.06106  -0.0596   0.9766   0.0773
  -4.000  -0.3079   0.06186   0.05739  -0.0576   0.9731   0.0811
  -3.750  -0.2712   0.05805   0.05321  -0.0643   0.9689   0.0914
  -3.500  -0.2374   0.05463   0.04952  -0.0689   0.9654   0.1046
  -3.250  -0.2091   0.05117   0.04592  -0.0717   0.9622   0.1188
  -3.000  -0.1871   0.04846   0.04311  -0.0729   0.9582   0.1332
  -2.750  -0.1570   0.04578   0.04024  -0.0756   0.9543   0.1600
  -2.500  -0.1258   0.04339   0.03768  -0.0781   0.9512   0.2006
  -1.750   0.0042   0.03462   0.02653  -0.0834   0.9406   0.0756
  -1.500   0.0440   0.03218   0.02372  -0.0854   0.9378   0.0717
  -1.250   0.0711   0.03108   0.02203  -0.0844   0.9334   0.0639
  -1.000   0.0997   0.03005   0.02072  -0.0842   0.9292   0.0627
  -0.750   0.1349   0.02885   0.01938  -0.0853   0.9257   0.0639
  -0.500   0.1644   0.02801   0.01860  -0.0857   0.9220   0.0713
  -0.250   0.1845   0.02752   0.01810  -0.0846   0.9171   0.0996
   0.000   0.2263   0.02468   0.01754  -0.0868   0.9147   1.0000
   0.250   0.2630   0.02528   0.01776  -0.0889   0.9109   1.0000
   0.500   0.2790   0.02577   0.01805  -0.0876   0.9047   1.0000
   0.750   0.3091   0.02632   0.01840  -0.0886   0.8999   1.0000
   1.000   0.3377   0.02693   0.01885  -0.0895   0.8949   1.0000
   1.250   0.3577   0.02748   0.01926  -0.0889   0.8888   1.0000
   1.500   0.3932   0.02810   0.01976  -0.0909   0.8847   1.0000
   1.750   0.4079   0.02874   0.02034  -0.0894   0.8782   1.0000
   2.000   0.4378   0.02934   0.02088  -0.0904   0.8730   1.0000
   2.250   0.4617   0.03002   0.02153  -0.0905   0.8672   1.0000
   2.500   0.4854   0.03064   0.02217  -0.0906   0.8608   1.0000
   2.750   0.5222   0.03128   0.02280  -0.0927   0.8567   1.0000
   3.000   0.5332   0.03200   0.02353  -0.0907   0.8484   1.0000
   3.250   0.5730   0.03257   0.02416  -0.0932   0.8441   1.0000
   3.500   0.5834   0.03333   0.02496  -0.0911   0.8349   1.0000
   3.750   0.6249   0.03385   0.02558  -0.0938   0.8306   1.0000
   4.000   0.6347   0.03465   0.02654  -0.0917   0.8209   1.0000
   4.250   0.6596   0.03533   0.02734  -0.0917   0.8134   1.0000
   4.500   0.6894   0.03587   0.02805  -0.0925   0.8062   1.0000
   4.750   0.7082   0.03659   0.02892  -0.0916   0.7966   1.0000
   5.000   0.7520   0.03680   0.02940  -0.0941   0.7911   1.0000
   5.250   0.7996   0.03595   0.02903  -0.0957   0.7774   1.0000
   5.500   0.8965   0.02259   0.01197  -0.0811   0.0558   1.0000
   5.750   0.9017   0.02414   0.01358  -0.0774   0.0487   1.0000
   6.000   0.9114   0.02543   0.01502  -0.0743   0.0463   1.0000
   6.250   0.9244   0.02706   0.01670  -0.0716   0.0442   1.0000
   6.500   0.9620   0.02935   0.01898  -0.0724   0.0429   1.0000
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