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HQ 1.0/10 AIRFOIL (hq1010-il)

HQ 1.0/10 AIRFOIL - Quabeck HQ 1.0/10 R/C sailplane airfoil


Airfoil hq1010-il
Details Dat file Parser  
(hq1010-il) HQ 1.0/10 AIRFOIL
Quabeck HQ 1.0/10 R/C sailplane airfoil
Max thickness 10% at 35% chord.
Max camber 1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 1.0/10 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0057000
 0.0050000 0.0085700
 0.0087500 0.0118000
 0.0125000 0.0144500
 0.0187500 0.0181800
 0.0250000 0.0212800
 0.0375000 0.0264000
 0.0500000 0.0305500
 0.0750000 0.0371900
 0.1000000 0.0423200
 0.1250000 0.0464100
 0.1500000 0.0496600
 0.1750000 0.0521800
 0.2000000 0.0541100
 0.2250000 0.0556200
 0.2500000 0.0568500
 0.2750000 0.0578700
 0.3000000 0.0586700
 0.3250000 0.0591900
 0.3500000 0.0594000
 0.3750000 0.0593200
 0.4000000 0.0589700
 0.4500000 0.0575800
 0.5000000 0.0552200
 0.5500000 0.0518700
 0.6000000 0.0476000
 0.6500000 0.0425200
 0.7000000 0.0368800
 0.7500000 0.0307300
 0.8000000 0.0243000
 0.8250000 0.0210300
 0.8500000 0.0178300
 0.8750000 0.0147300
 0.9000000 0.0116700
 0.9250000 0.0087300
 0.9500000 0.0056700
 0.9750000 0.0026900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0046000
 0.0050000 -.0068100
 0.0087500 -.0093700
 0.0125000 -.0114300
 0.0187500 -.0142500
 0.0250000 -.0164500
 0.0375000 -.0199700
 0.0500000 -.0227200
 0.0750000 -.0270200
 0.1000000 -.0302800
 0.1250000 -.0328600
 0.1500000 -.0348900
 0.1750000 -.0364500
 0.2000000 -.0376200
 0.2250000 -.0385100
 0.2500000 -.0391900
 0.2750000 -.0397300
 0.3000000 -.0401100
 0.3250000 -.0402800
 0.3500000 -.0402000
 0.3750000 -.0398700
 0.4000000 -.0393300
 0.4500000 -.0376600
 0.5000000 -.0352300
 0.5500000 -.0320400
 0.6000000 -.0281800
 0.6500000 -.0238400
 0.7000000 -.0193000
 0.7500000 -.0147200
 0.8000000 -.0104000
 0.8250000 -.0084300
 0.8500000 -.0066600
 0.8750000 -.0051500
 0.9000000 -.0038000
 0.9250000 -.0027200
 0.9500000 -.0015800
 0.9750000 -.0006500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for HQ 1.0/10 AIRFOIL (hq1010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq1010-il50,000932.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq1010-il50,000532.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq1010-il100,000947.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq1010-il100,000545.1 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq1010-il200,000963.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq1010-il200,000555.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq1010-il500,000979.1 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq1010-il500,000568.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq1010-il1,000,000985.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq1010-il1,000,000578 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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