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RAF 89 AIRFOIL (raf89-il)

RAF 89 AIRFOIL - RAF-89 airfoil


Airfoil raf89-il
Details Dat file Parser  
(raf89-il) RAF 89 AIRFOIL
RAF-89 airfoil
Max thickness 25% at 30% chord.
Max camber 1.6% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAF 89 AIRFOIL
       13.       13.

 0.0000000 0.0000000
 0.0250000 0.0523200
 0.0500000 0.0730500
 0.1000000 0.1003900
 0.2000000 0.1294800
 0.3000000 0.1393700
 0.4000000 0.1375600
 0.5000000 0.1275500
 0.6000000 0.1091400
 0.7000000 0.0840300
 0.8000000 0.0565200
 0.9000000 0.0285100
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0250000 -.0484800
 0.0500000 -.0663500
 0.1000000 -.0878100
 0.2000000 -.1074200
 0.3000000 -.1106300
 0.4000000 -.1054400
 0.5000000 -.0947500
 0.6000000 -.0767600
 0.7000000 -.0582700
 0.8000000 -.0382800
 0.9000000 -.0192900
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RAF 89 AIRFOIL (raf89-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   raf89-il50,00091.6 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf89-il50,00057 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   raf89-il100,000918.7 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   raf89-il100,000527.4 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   raf89-il200,000945.7 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf89-il200,000536 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   raf89-il500,000950.9 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf89-il500,000539.7 at α=11.25°Mach=0 Ncrit=5Xfoil predictionDetails
   raf89-il1,000,000956.2 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   raf89-il1,000,000545.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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