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Coanda 1 (coanda1-il)

Coanda 1 - Coanda 1 airfoil


Airfoil coanda1-il
Details Dat file Parser  
(coanda1-il) Coanda 1
Coanda 1 airfoil
Max thickness 5.7% at 30% chord.
Max camber 2.9% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Coanda 1
1.0000     0.0100
0.9500     0.0195
0.9000     0.0270
0.8000     0.0400
0.7000     0.0500
0.6000     0.0585
0.5000     0.0650
0.4000     0.0695
0.3000     0.0700
0.2000     0.0670
0.1500     0.0632
0.1000     0.0570
0.0750     0.0515
0.0500     0.0435
0.0250     0.0325
0.0125     0.0240
0.0000     0.0140
0.0125     0.0070
0.0250     0.0030
0.0500     0.0000
0.0750     0.0030
0.1000     0.0070
0.1500     0.0100
0.2000     0.0115
0.3000     0.0135
0.4000     0.0135
0.5000     0.0125
0.6000     0.0110
0.7000     0.0085
0.8000     0.0040
0.9000     0.0000
0.9500     0.0030
1.0000     0.0100
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Selig format dat file

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Polars for Coanda 1 (coanda1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   coanda1-il50,000938 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   coanda1-il50,000537.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   coanda1-il100,000954.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   coanda1-il100,000547.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   coanda1-il200,000960.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   coanda1-il200,000545.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   coanda1-il500,000963.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   coanda1-il500,000551.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   coanda1-il1,000,000960.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   coanda1-il1,000,000557.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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