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USA 51 AIRFOIL (usa51-il)

USA 51 AIRFOIL - USA-51 airfoil


Airfoil usa51-il
Details Dat file Parser  
(usa51-il) USA 51 AIRFOIL
USA-51 airfoil
Max thickness 9.3% at 30% chord.
Max camber 2.6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 51 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0157000
 0.0250000 0.0240000
 0.0500000 0.0390000
 0.0750000 0.0480000
 0.1000000 0.0536000
 0.1500000 0.0626000
 0.2000000 0.0687000
 0.3000000 0.0723000
 0.4000000 0.0687000
 0.5000000 0.0630000
 0.6000000 0.0547000
 0.7000000 0.0437000
 0.8000000 0.0317000
 0.9000000 0.0178000
 0.9500000 0.0090000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0087000
 0.0250000 -.0117000
 0.0500000 -.0157000
 0.0750000 -.0180000
 0.1000000 -.0193000
 0.1500000 -.0207000
 0.2000000 -.0210000
 0.3000000 -.0210000
 0.4000000 -.0200000
 0.5000000 -.0183000
 0.6000000 -.0160000
 0.7000000 -.0123000
 0.8000000 -.0083000
 0.9000000 -.0043000
 0.9500000 -.0025000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for USA 51 AIRFOIL (usa51-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa51-il50,000932.4 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa51-il50,000535.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa51-il100,000948.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   usa51-il100,000548.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa51-il200,000963.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa51-il200,000560.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa51-il500,000980.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   usa51-il500,000573 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa51-il1,000,000992.1 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa51-il1,000,000586.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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