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I.S.A. 961 (isa961-il)

I.S.A. 961 - I.S.A. 961 airfoil


Airfoil isa961-il
Details Dat file Parser  
(isa961-il) I.S.A. 961
I.S.A. 961 airfoil
Max thickness 9.3% at 20% chord.
Max camber 4.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
I.S.A. 961
1.0000     0.0037
0.9500     0.0168
0.9000     0.0277
0.8000     0.0490
0.7000     0.0675
0.6000     0.0825
0.5000     0.0937
0.4000     0.1005
0.3000     0.1030
0.2000     0.0987
0.1500     0.0925
0.1000     0.0807
0.0750     0.0740
0.0500     0.0620
0.0250     0.0490
0.0125     0.0372
0.0000     0.0162
0.0125     0.0080
0.0250     0.0038
0.0500     0.0000
0.0750     0.0000
0.1000     0.0000
0.1500     0.0030
0.2000     0.0060
0.3000     0.0105
0.4000     0.0122
0.5000     0.0112
0.6000     0.0097
0.7000     0.0077
0.8000     0.0047
0.9000     0.0020
0.9500     0.0001
1.0000     0.0000
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Selig format dat file

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Polars for I.S.A. 961 (isa961-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   isa961-il50,000934.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   isa961-il50,000539.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   isa961-il100,000955.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   isa961-il100,000553.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   isa961-il200,000970.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   isa961-il200,000563 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   isa961-il500,000980 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   isa961-il500,000575.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   isa961-il1,000,000990.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   isa961-il1,000,000588.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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