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USA 26 AIRFOIL (usa26-il)

USA 26 AIRFOIL - USA-26 airfoil


Airfoil usa26-il
Details Dat file Parser  
(usa26-il) USA 26 AIRFOIL
USA-26 airfoil
Max thickness 9.8% at 19.9% chord.
Max camber 4.3% at 39.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 26 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0123000 0.0181400
 0.0246800 0.0290700
 0.0495100 0.0445400
 0.0743800 0.0564200
 0.0992800 0.0650900
 0.1491500 0.0774400
 0.1990500 0.0861900
 0.2989900 0.0913900
 0.3990300 0.0883900
 0.4991100 0.0810900
 0.5992100 0.0721900
 0.6993400 0.0599900
 0.7995099 0.0443900
 0.8997200 0.0252000
 0.9498500 0.0132500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0126400 -.0125600
 0.0251600 -.0151200
 0.0501700 -.0158500
 0.0751700 -.0159700
 0.1001800 -.0166000
 0.1501700 -.0150500
 0.2001300 -.0120000
 0.3000500 -.0049000
 0.4000200 -.0016000
 0.5000500 -.0042000
 0.6000900 -.0086000
 0.7001000 -.0090000
 0.8000900 -.0084000
 0.9000700 -.0063000
 0.9500400 -.0032500
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for USA 26 AIRFOIL (usa26-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa26-il50,000927.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa26-il50,000535.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa26-il100,000949.8 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa26-il100,000552.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   usa26-il200,000969.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa26-il200,000569.1 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa26-il500,000995.9 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   usa26-il500,000592.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa26-il1,000,0009117.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa26-il1,000,0005108.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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