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HQ 3.5/14 AIRFOIL (hq3514-il)

HQ 3.5/14 AIRFOIL - Quabeck HQ 3.5/14 R/C sailplane airfoil


Airfoil hq3514-il
Details Dat file Parser  
(hq3514-il) HQ 3.5/14 AIRFOIL
Quabeck HQ 3.5/14 R/C sailplane airfoil
Max thickness 14% at 35% chord.
Max camber 3.5% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 3.5/14 AIRFOIL
       20.       20.

 0.0000000 0.0000000
 0.0050000 0.0153600
 0.0125000 0.0245000
 0.0250000 0.0351200
 0.0500000 0.0511800
 0.1000000 0.0714900
 0.1500000 0.0838700
 0.2000000 0.0928500
 0.2500000 0.0980900
 0.3000000 0.1015100
 0.3500000 0.1036000
 0.4000000 0.1028400
 0.5000000 0.0985600
 0.6000000 0.0872400
 0.7000000 0.0698900
 0.8000000 0.0485400
 0.8500000 0.0364700
 0.9000000 0.0247300
 0.9500000 0.0117900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0050000 -.0074200
 0.0125000 -.0128400
 0.0250000 -.0180800
 0.0500000 -.0237600
 0.1000000 -.0294900
 0.1500000 -.0338300
 0.2000000 -.0352100
 0.2500000 -.0364900
 0.3000000 -.0365300
 0.3500000 -.0364000
 0.4000000 -.0357600
 0.5000000 -.0285600
 0.6000000 -.0193400
 0.7000000 -.0084100
 0.8000000 0.0000000
 0.8500000 0.0024900
 0.9000000 0.0032700
 0.9500000 0.0025500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for HQ 3.5/14 AIRFOIL (hq3514-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq3514-il50,000929.4 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3514-il50,000533.1 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3514-il100,000955.8 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3514-il100,000554.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3514-il200,000980 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3514-il200,000571.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3514-il500,0009100.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3514-il500,000586.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3514-il1,000,0009112.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3514-il1,000,000599.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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