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A18 (original) (a18-il)

A18 (original) - Archer A18 F1C free flight airfoil(original)


Airfoil a18-il
Details Dat file Parser  
(a18-il) A18 (original)
Archer A18 F1C free flight airfoil(original)
Max thickness 7.3% at 30% chord.
Max camber 3.9% at 45% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
A18 (original)
   1.00000   0.00614
   0.95000   0.01817
   0.90000   0.02858
   0.80000   0.04624
   0.70000   0.06056
   0.60000   0.07197
   0.55000   0.07612
   0.50000   0.07975
   0.45000   0.08293
   0.40000   0.08376
   0.35000   0.08466
   0.30000   0.08383
   0.25000   0.08065
   0.20000   0.07601
   0.15000   0.07026
   0.10000   0.06234
   0.07500   0.05660
   0.05000   0.04923
   0.02500   0.03947
   0.01250   0.03239
   0.00000   0.01865
   0.01250   0.00781
   0.02500   0.00357
   0.05000   0.00075
   0.07500   0.00000
   0.10000   0.00006
   0.15000   0.00200
   0.20000   0.00475
   0.25000   0.00806
   0.30000   0.01038
   0.35000   0.01353
   0.40000   0.01657
   0.45000   0.01780
   0.50000   0.01884
   0.55000   0.01980
   0.60000   0.01998
   0.70000   0.01924
   0.80000   0.01452
   0.90000   0.00813
   0.95000   0.00434
   1.00000   0.00000
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Polars for A18 (original) (a18-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   a18-il50,000944 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   a18-il50,000544.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18-il100,000965 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   a18-il100,000563.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18-il200,000986.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   a18-il200,000580.7 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18-il500,0009111.9 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   a18-il500,000599.6 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   a18-il1,000,0009124.7 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   a18-il1,000,0005109.6 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
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