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I.S.A. 571 (isa571-il)

I.S.A. 571 - I.S.A. 571 airfoil


Airfoil isa571-il
Details Dat file Parser  
(isa571-il) I.S.A. 571
I.S.A. 571 airfoil
Max thickness 7.4% at 30% chord.
Max camber 3.6% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
I.S.A. 571
1.0000     0.0030
0.9500     0.0150
0.9000     0.0250
0.8000     0.0410
0.7000     0.0532
0.6000     0.0632
0.5000     0.0717
0.4000     0.0772
0.3000     0.0802
0.2000     0.0780
0.1500     0.0725
0.1000     0.0640
0.0750     0.0570
0.0500     0.0487
0.0250     0.0355
0.0125     0.0267
0.0000     0.0100
0.0125     0.0024
0.0250     0.0000
0.0500     0.0000
0.0750     0.0000
0.1000     0.0020
0.1500     0.0040
0.2000     0.0055
0.3000     0.0065
0.4000     0.0070
0.5000     0.0070
0.6000     0.0062
0.7000     0.0055
0.8000     0.0044
0.9000     0.0025
0.9500     0.0015
1.0000     0.0000
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Selig format dat file

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Polars for I.S.A. 571 (isa571-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   isa571-il50,000935.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   isa571-il50,000539.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   isa571-il100,000951.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   isa571-il100,000554.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   isa571-il200,000969.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   isa571-il200,000570.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   isa571-il500,000993.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   isa571-il500,000589.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   isa571-il1,000,0009109.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   isa571-il1,000,0005100.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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