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HQ 2.5/8 AIRFOIL (hq258-il)

HQ 2.5/8 AIRFOIL - Quabeck HQ 2.5/8 R/C sailplane airfoil


Airfoil hq258-il
Details Dat file Parser  
(hq258-il) HQ 2.5/8 AIRFOIL
Quabeck HQ 2.5/8 R/C sailplane airfoil
Max thickness 8% 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 2.5/8 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0050100
 0.0050000 0.0078600
 0.0087500 0.0111600
 0.0125000 0.0139100
 0.0187500 0.0178100
 0.0250000 0.0211000
 0.0375000 0.0266300
 0.0500000 0.0311400
 0.0750000 0.0383600
 0.1000000 0.0438900
 0.1250000 0.0483000
 0.1500000 0.0518400
 0.1750000 0.0547300
 0.2000000 0.0570800
 0.2250000 0.0589800
 0.2500000 0.0605200
 0.2750000 0.0617700
 0.3000000 0.0627600
 0.3250000 0.0634500
 0.3500000 0.0638300
 0.3750000 0.0639600
 0.4000000 0.0638500
 0.4500000 0.0629700
 0.5000000 0.0611500
 0.5500000 0.0583500
 0.6000000 0.0545800
 0.6500000 0.0498900
 0.7000000 0.0444300
 0.7500000 0.0381800
 0.8000000 0.0312400
 0.8250000 0.0275200
 0.8500000 0.0237300
 0.8750000 0.0199000
 0.9000000 0.0159900
 0.9250000 0.0120700
 0.9500000 0.0080000
 0.9750000 0.0038900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0026700
 0.0050000 -.0039100
 0.0087500 -.0053800
 0.0125000 -.0065400
 0.0187500 -.0080100
 0.0250000 -.0090200
 0.0375000 -.0105100
 0.0500000 -.0115500
 0.0750000 -.0130300
 0.1000000 -.0140600
 0.1250000 -.0148500
 0.1500000 -.0154400
 0.1750000 -.0158600
 0.2000000 -.0161300
 0.2250000 -.0163000
 0.2500000 -.0163800
 0.2750000 -.0163900
 0.3000000 -.0163300
 0.3250000 -.0161600
 0.3500000 -.0158600
 0.3750000 -.0154000
 0.4000000 -.0147800
 0.4500000 -.0132100
 0.5000000 -.0111800
 0.5500000 -.0087600
 0.6000000 -.0060300
 0.6500000 -.0031900
 0.7000000 -.0005000
 0.7500000 0.0018300
 0.8000000 0.0035000
 0.8250000 0.0039800
 0.8500000 0.0041800
 0.8750000 0.0040300
 0.9000000 0.0036600
 0.9250000 0.0029500
 0.9500000 0.0022400
 0.9750000 0.0012500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for HQ 2.5/8 AIRFOIL (hq258-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq258-il50,000939.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq258-il50,000540.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq258-il100,000959.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq258-il100,000557.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq258-il200,000980.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq258-il200,000574 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq258-il500,0009108.1 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq258-il500,000590.5 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq258-il1,000,0009124.1 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq258-il1,000,000596.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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