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USA 22 AIRFOIL (usa22-il)

USA 22 AIRFOIL - USA-22 airfoil


Airfoil usa22-il
Details Dat file Parser  
(usa22-il) USA 22 AIRFOIL
USA-22 airfoil
Max thickness 9.1% at 19.9% chord.
Max camber 4.4% at 39.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 22 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0122500 0.0171800
 0.0246000 0.0273600
 0.0493700 0.0437200
 0.0742000 0.0552800
 0.0990700 0.0644400
 0.1489000 0.0761600
 0.1988000 0.0828800
 0.2987300 0.0873300
 0.3988000 0.0827800
 0.4989200 0.0742300
 0.5990900 0.0626900
 0.6992900 0.0491400
 0.7995000 0.0345900
 0.8997400 0.0180500
 0.9498600 0.0097700
 1.0000000 0.0005000

 0.0000000 0.0000000
 0.0126200 -.0083200
 0.0251600 -.0111400
 0.0501900 -.0127700
 0.0751900 -.0134100
 0.1002000 -.0135500
 0.1501600 -.0113200
 0.2001200 -.0081000
 0.2999900 0.0008500
 0.3999200 0.0058000
 0.4999200 0.0052500
 0.5999300 0.0047000
 0.6999400 0.0041500
 0.7999600 0.0026000
 0.8999800 0.0010500
 0.9500000 -.0000200
 1.0000000 -.0005000
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Lednicer format dat file
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Polars for USA 22 AIRFOIL (usa22-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa22-il50,000932.5 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa22-il50,000537.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa22-il100,000953.8 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa22-il100,000555.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   usa22-il200,000973 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   usa22-il200,000573.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   usa22-il500,000999.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa22-il500,000596.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa22-il1,000,0009119.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa22-il1,000,0005112.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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