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HQ 2.5/9 AIRFOIL (hq259-il)

HQ 2.5/9 AIRFOIL - Quabeck HQ 2.5/9 R/C sailplane airfoil


Airfoil hq259-il
Details Dat file Parser  
(hq259-il) HQ 2.5/9 AIRFOIL
Quabeck HQ 2.5/9 R/C sailplane airfoil
Max thickness 9% at 35% chord.
Max camber 2.5% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 2.5/9 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0054600
 0.0050000 0.0085400
 0.0087500 0.0121300
 0.0125000 0.0151300
 0.0187500 0.0193900
 0.0250000 0.0229600
 0.0375000 0.0289500
 0.0500000 0.0338200
 0.0750000 0.0415800
 0.1000000 0.0475100
 0.1250000 0.0522400
 0.1500000 0.0560400
 0.1750000 0.0591500
 0.2000000 0.0616600
 0.2250000 0.0636900
 0.2500000 0.0653100
 0.2750000 0.0666400
 0.3000000 0.0676800
 0.3250000 0.0684100
 0.3500000 0.0688100
 0.3750000 0.0689100
 0.4000000 0.0687500
 0.4500000 0.0677000
 0.5000000 0.0656500
 0.5500000 0.0625300
 0.6000000 0.0583600
 0.6500000 0.0532000
 0.7000000 0.0472200
 0.7500000 0.0404300
 0.8000000 0.0329700
 0.8250000 0.0290200
 0.8500000 0.0250000
 0.8750000 0.0209400
 0.9000000 0.0167900
 0.9250000 0.0126500
 0.9500000 0.0083600
 0.9750000 0.0040500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0031600
 0.0050000 -.0046500
 0.0087500 -.0064000
 0.0125000 -.0078000
 0.0187500 -.0096100
 0.0250000 -.0108900
 0.0375000 -.0128400
 0.0500000 -.0142300
 0.0750000 -.0162400
 0.1000000 -.0176800
 0.1250000 -.0187900
 0.1500000 -.0196500
 0.1750000 -.0202800
 0.2000000 -.0207200
 0.2250000 -.0210200
 0.2500000 -.0212100
 0.2750000 -.0213100
 0.3000000 -.0213100
 0.3250000 -.0211700
 0.3500000 -.0208600
 0.3750000 -.0203600
 0.4000000 -.0196900
 0.4500000 -.0179500
 0.5000000 -.0156800
 0.5500000 -.0129300
 0.6000000 -.0098100
 0.6500000 -.0065000
 0.7000000 -.0033300
 0.7500000 -.0004800
 0.8000000 0.0017300
 0.8250000 0.0024800
 0.8500000 0.0029600
 0.8750000 0.0030700
 0.9000000 0.0029300
 0.9250000 0.0024200
 0.9500000 0.0019100
 0.9750000 0.0011000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for HQ 2.5/9 AIRFOIL (hq259-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq259-il50,000938.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq259-il50,000539.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq259-il100,000958.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq259-il100,000556.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq259-il200,000980 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq259-il200,000573 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq259-il500,0009106.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq259-il500,000588.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq259-il1,000,0009122 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   hq259-il1,000,000592.4 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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