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USA 98 AIRFOIL (usa98-il)

USA 98 AIRFOIL - USA-98 airfoil


Airfoil usa98-il
Details Dat file Parser  
(usa98-il) USA 98 AIRFOIL
USA-98 airfoil
Max thickness 14.3% at 30% chord.
Max camber 6.4% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 98 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0250000 0.0410000
 0.0500000 0.0580000
 0.1000000 0.0830000
 0.2000000 0.1120000
 0.3000000 0.1260000
 0.4000000 0.1290000
 0.5000000 0.1230000
 0.6000000 0.1100000
 0.7000000 0.0910000
 0.8000000 0.0690000
 0.9000000 0.0450000
 1.0000000 0.0090000

 0.0000000 0.0000000
 0.0250000 -.0340000
 0.0500000 -.0375000
 0.1000000 -.0360000
 0.2000000 -.0295000
 0.3000000 -.0170000
 0.4000000 -.0030000
 0.5000000 0.0090000
 0.6000000 0.0160000
 0.7000000 0.0190000
 0.8000000 0.0170000
 0.9000000 0.0090000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for USA 98 AIRFOIL (usa98-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa98-il50,00098.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa98-il50,000526.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa98-il100,000954.2 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa98-il100,000559.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa98-il200,000984.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   usa98-il200,000584.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa98-il500,0009120.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa98-il500,0005112.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa98-il1,000,0009147.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa98-il1,000,0005124.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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