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

HQ 3.0/13 AIRFOIL (hq3013-il)

HQ 3.0/13 AIRFOIL - Quabeck HQ 3.0/13 R/C sailplane airfoil


Airfoil hq3013-il
Details Dat file Parser  
(hq3013-il) HQ 3.0/13 AIRFOIL
Quabeck HQ 3.0/13 R/C sailplane airfoil
Max thickness 13% at 35% chord.
Max camber 3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 3.0/13 AIRFOIL
       39.       39.

 0.0000000 0.0000000
 0.0025000 0.0086000
 0.0050000 0.0132500
 0.0087500 0.0183000
 0.0125000 0.0222300
 0.0187500 0.0277200
 0.0250000 0.0323500
 0.0375000 0.0401200
 0.0500000 0.0465700
 0.0750000 0.0569000
 0.1000000 0.0648400
 0.1250000 0.0711700
 0.1500000 0.0762800
 0.1750000 0.0805000
 0.2000000 0.0839700
 0.2250000 0.0867500
 0.2500000 0.0889500
 0.2750000 0.0907300
 0.3000000 0.0921000
 0.3250000 0.0930500
 0.3500000 0.0935300
 0.3750000 0.0936000
 0.4000000 0.0933200
 0.4500000 0.0917500
 0.5000000 0.0887700
 0.5500000 0.0842900
 0.6000000 0.0783700
 0.6500000 0.0711000
 0.7000000 0.0627900
 0.7500000 0.0533400
 0.8000000 0.0433400
 0.8250000 0.0380700
 0.8500000 0.0327800
 0.8750000 0.0274900
 0.9000000 0.0220600
 0.9250000 0.0165900
 0.9500000 0.0109200
 0.9750000 0.0052400
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0025000 -.0050000
 0.0050000 -.0073100
 0.0087500 -.0100200
 0.0125000 -.0122200
 0.0187500 -.0151200
 0.0250000 -.0172500
 0.0375000 -.0205400
 0.0500000 -.0229600
 0.0750000 -.0265600
 0.1000000 -.0291900
 0.1250000 -.0312500
 0.1500000 -.0328700
 0.1750000 -.0340800
 0.2000000 -.0349500
 0.2250000 -.0355800
 0.2500000 -.0360000
 0.2750000 -.0362400
 0.3000000 -.0363700
 0.3250000 -.0364100
 0.3500000 -.0363400
 0.3750000 -.0359100
 0.4000000 -.0350600
 0.4500000 -.0324300
 0.5000000 -.0287200
 0.5500000 -.0243400
 0.6000000 -.0195200
 0.6500000 -.0146300
 0.7000000 -.0099100
 0.7500000 -.0055300
 0.8000000 -.0017800
 0.8250000 -.0002900
 0.8500000 0.0008500
 0.8750000 0.0014800
 0.9000000 0.0018000
 0.9250000 0.0016300
 0.9500000 0.0014900
 0.9750000 0.0009500
 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 3.5/13 AIRFOILPreviewDetails
EPPLER 68 AIRFOILPreviewDetails
S4233-136-84PreviewDetails
MH 201 13.08%PreviewDetails
DELFT DU84-132V3 AIRFOIL (MEASURED)PreviewDetails
E197 (13.49%)PreviewDetails
EPPLER E854 AIRFOILPreviewDetails
NREL's S801 AirfoilPreviewDetails
HQ 3.0/14 AIRFOILPreviewDetails
HQ 3.0/12 AIRFOILPreviewDetails

Polars for HQ 3.0/13 AIRFOIL (hq3013-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq3013-il50,000932.5 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3013-il50,000535.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3013-il100,000955.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3013-il100,000555.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3013-il200,000979.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3013-il200,000573.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3013-il500,0009106 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3013-il500,000586.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hq3013-il1,000,0009115.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hq3013-il1,000,000597.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit