Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 1.0/8 AIRFOIL (hq108-il)

HQ 1.0/8 AIRFOIL - Quabeck HQ 1.0/8 R/C sailplane airfoil


Airfoil hq108-il
Details Dat file Parser  
(hq108-il) HQ 1.0/8 AIRFOIL
Quabeck HQ 1.0/8 R/C sailplane airfoil
Max thickness 8% 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 1.0/8 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0046700
 0.0050000 0.0070200
 0.0087500 0.0096800
 0.0125000 0.0118800
 0.0187500 0.0149600
 0.0250000 0.0175300
 0.0375000 0.0217800
 0.0500000 0.0252300
 0.0750000 0.0307700
 0.1000000 0.0350700
 0.1250000 0.0385000
 0.1500000 0.0412100
 0.1750000 0.0433000
 0.2000000 0.0449200
 0.2250000 0.0462100
 0.2500000 0.0472700
 0.2750000 0.0481700
 0.3000000 0.0488600
 0.3250000 0.0492900
 0.3500000 0.0494500
 0.3750000 0.0493800
 0.4000000 0.0491100
 0.4500000 0.0480300
 0.5000000 0.0461700
 0.5500000 0.0435000
 0.6000000 0.0400400
 0.6500000 0.0359000
 0.7000000 0.0312600
 0.7500000 0.0261800
 0.8000000 0.0208300
 0.8250000 0.0180900
 0.8500000 0.0153700
 0.8750000 0.0127200
 0.9000000 0.0100900
 0.9250000 0.0075500
 0.9500000 0.0049100
 0.9750000 0.0023400
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0035800
 0.0050000 -.0052700
 0.0087500 -.0072400
 0.0125000 -.0088400
 0.0187500 -.0110000
 0.0250000 -.0126800
 0.0375000 -.0153600
 0.0500000 -.0174400
 0.0750000 -.0206400
 0.1000000 -.0230500
 0.1250000 -.0249600
 0.1500000 -.0264700
 0.1750000 -.0276200
 0.2000000 -.0284900
 0.2250000 -.0291500
 0.2500000 -.0296500
 0.2750000 -.0300300
 0.3000000 -.0302800
 0.3250000 -.0303700
 0.3500000 -.0302700
 0.3750000 -.0299800
 0.4000000 -.0295200
 0.4500000 -.0281500
 0.5000000 -.0262000
 0.5500000 -.0236700
 0.6000000 -.0206300
 0.6500000 -.0172100
 0.7000000 -.0136800
 0.7500000 -.0101600
 0.8000000 -.0069200
 0.8250000 -.0054800
 0.8500000 -.0042000
 0.8750000 -.0031400
 0.9000000 -.0022200
 0.9250000 -.0015400
 0.9500000 -.0008300
 0.9750000 -.0003000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

HQ 1.5/8 AIRFOILPreviewDetails
S2055PreviewDetails
DU86-084/18 8.44%PreviewDetails
NACA 64-208PreviewDetails
HQ 1.5/8.5 AIRFOILPreviewDetails
PROPFAN CRUISE MISSILE WING AIRFOILPreviewDetails
NACA 64-108 AIRFOILPreviewDetails
MH 23 8%PreviewDetails
S2062 8%PreviewDetails
S2060 8%PreviewDetails

Polars for HQ 1.0/8 AIRFOIL (hq108-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq108-il50,000933.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq108-il50,000533.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq108-il100,000948 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq108-il100,000544.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hq108-il200,000962.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hq108-il200,000554.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq108-il500,000978.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq108-il500,000563.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hq108-il1,000,000985 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq108-il1,000,000572.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit