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

HQ 2.0/8 AIRFOIL (hq208-il)

HQ 2.0/8 AIRFOIL - Quabeck HQ 2.0/8 R/C sailplane airfoil


Airfoil hq208-il
Details Dat file Parser  
(hq208-il) HQ 2.0/8 AIRFOIL
Quabeck HQ 2.0/8 R/C sailplane airfoil
Max thickness 8% at 35% chord.
Max camber 2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 2.0/8 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0053600
 0.0050000 0.0083200
 0.0087500 0.0115500
 0.0125000 0.0140200
 0.0187500 0.0174700
 0.0250000 0.0203300
 0.0375000 0.0251300
 0.0500000 0.0291800
 0.0750000 0.0358100
 0.1000000 0.0410700
 0.1250000 0.0452700
 0.1500000 0.0485900
 0.1750000 0.0511500
 0.2000000 0.0531400
 0.2250000 0.0547400
 0.2500000 0.0560600
 0.2750000 0.0571800
 0.3000000 0.0580800
 0.3250000 0.0587000
 0.3500000 0.0590200
 0.3750000 0.0590900
 0.4000000 0.0589400
 0.4500000 0.0579800
 0.5000000 0.0561300
 0.5500000 0.0533600
 0.6000000 0.0497000
 0.6500000 0.0452300
 0.7000000 0.0400600
 0.7500000 0.0341700
 0.8000000 0.0276800
 0.8250000 0.0242200
 0.8500000 0.0207600
 0.8750000 0.0173600
 0.9000000 0.0139500
 0.9250000 0.0105400
 0.9500000 0.0069900
 0.9750000 0.0034000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0030000
 0.0050000 -.0043800
 0.0087500 -.0059800
 0.0125000 -.0072700
 0.0187500 -.0089700
 0.0250000 -.0102100
 0.0375000 -.0121300
 0.0500000 -.0135500
 0.0750000 -.0156400
 0.1000000 -.0171500
 0.1250000 -.0182900
 0.1500000 -.0191500
 0.1750000 -.0197800
 0.2000000 -.0202300
 0.2250000 -.0205700
 0.2500000 -.0208000
 0.2750000 -.0209400
 0.3000000 -.0209900
 0.3250000 -.0209300
 0.3500000 -.0207400
 0.3750000 -.0203500
 0.4000000 -.0198000
 0.4500000 -.0182800
 0.5000000 -.0162400
 0.5500000 -.0137600
 0.6000000 -.0109100
 0.6500000 -.0078700
 0.7000000 -.0049000
 0.7500000 -.0021900
 0.8000000 0.0000100
 0.8250000 0.0008000
 0.8500000 0.0013600
 0.8750000 0.0016200
 0.9000000 0.0016900
 0.9250000 0.0014600
 0.9500000 0.0012300
 0.9750000 0.0007500
 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 2.5/8 AIRFOILPreviewDetails
HQ 1.5/8 AIRFOILPreviewDetails
MH 30 7.84%PreviewDetails
WORTMANN FX 80-080PreviewDetails
HQ 1.5/8.5 AIRFOILPreviewDetails
S2060 8%PreviewDetails
SD2030-086-88PreviewDetails
S2055PreviewDetails
S2062 8%PreviewDetails
GOE 795 AIRFOILPreviewDetails

Polars for HQ 2.0/8 AIRFOIL (hq208-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq208-il50,000937.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq208-il50,000538.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq208-il100,000955.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq208-il100,000553.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq208-il200,000974.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hq208-il200,000568.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq208-il500,000998.4 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   hq208-il500,000583.4 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq208-il1,000,0009112.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq208-il1,000,000584.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit