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USA 33 AIRFOIL (usa33-il)

USA 33 AIRFOIL - USA-33 airfoil


Airfoil usa33-il
Details Dat file Parser  
(usa33-il) USA 33 AIRFOIL
USA-33 airfoil
Max thickness 14.2% at 29.9% chord.
Max camber 4.9% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 33 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0120700 0.0361400
 0.0243800 0.0512900
 0.0491900 0.0675900
 0.0740200 0.0813900
 0.0988900 0.0921900
 0.1487300 0.1057800
 0.1986300 0.1143800
 0.2985700 0.1195800
 0.3986100 0.1157800
 0.4987600 0.1029900
 0.5989700 0.0861900
 0.6992000 0.0663900
 0.7994600 0.0445900
 0.8997100 0.0238000
 0.9498300 0.0124000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0127900 -.0238500
 0.0253700 -.0307000
 0.0504100 -.0344000
 0.0754300 -.0360900
 0.1004300 -.0357900
 0.1503700 -.0312000
 0.2003100 -.0256000
 0.3002700 -.0224000
 0.4002900 -.0242000
 0.5003200 -.0270000
 0.6003500 -.0288000
 0.7003300 -.0276000
 0.8002600 -.0214000
 0.9001500 -.0122000
 0.9500800 -.0066000
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for USA 33 AIRFOIL (usa33-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa33-il50,00097.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa33-il50,000527.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   usa33-il100,000945.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa33-il100,000547.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   usa33-il200,000966.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa33-il200,000560.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa33-il500,000985.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa33-il500,000567.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa33-il1,000,000993.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa33-il1,000,000567.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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