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NACA 2.5411 (naca2411-il)

NACA 2.5411 - NACA 2411 airfoil


Airfoil naca2411-il
Details Dat file Parser  
(naca2411-il) NACA 2.5411
NACA 2411 airfoil
Max thickness 11% at 29.5% chord.
Max camber 2.5% at 39.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  NACA 2.5411     
  1.00000  0.00000
  0.99730  0.00059
  0.98918  0.00235
  0.97578  0.00520
  0.95720  0.00906
  0.93365  0.01380
  0.90535  0.01927
  0.87260  0.02532
  0.83577  0.03175
  0.79520  0.03839
  0.75138  0.04506
  0.70475  0.05158
  0.65583  0.05777
  0.60513  0.06347
  0.55322  0.06852
  0.50067  0.07276
  0.44807  0.07606
  0.39597  0.07830
  0.34455  0.07912
  0.29485  0.07831
  0.24745  0.07588
  0.20292  0.07193
  0.16175  0.06659
  0.12448  0.06006
  0.09148  0.05253
  0.06317  0.04427
  0.03985  0.03553
  0.02170  0.02654
  0.00897  0.01752
  0.00172  0.00862
  0.00000  0.00000
  0.00375 -0.00794
  0.01290 -0.01483
  0.02723 -0.02061
  0.04662 -0.02531
  0.07080 -0.02893
  0.09948 -0.03151
  0.13238 -0.03310
  0.16912 -0.03379
  0.20932 -0.03368
  0.25255 -0.03291
  0.29842 -0.03165
  0.34642 -0.03005
  0.39612 -0.02830
  0.44740 -0.02637
  0.49933 -0.02415
  0.55132 -0.02174
  0.60280 -0.01925
  0.65320 -0.01677
  0.70198 -0.01436
  0.74862 -0.01208
  0.79257 -0.00994
  0.83337 -0.00798
  0.87053 -0.00621
  0.90368 -0.00463
  0.93238 -0.00326
  0.95633 -0.00211
  0.97528 -0.00120
  0.98895 -0.00054
  0.99723 -0.00013
  1.00000  0.00000
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Polars for NACA 2.5411 (naca2411-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2411-il50,000934.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2411-il50,000535.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2411-il100,000952.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2411-il100,000552.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2411-il200,000971.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2411-il200,000567.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2411-il500,000995.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2411-il500,000586.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2411-il1,000,0009113.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2411-il1,000,000597.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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