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

HQ 0/10 AIRFOIL (hq010-il)

HQ 0/10 AIRFOIL - Quabeck HQ 0/10 R/C sailplane airfoil


Airfoil hq010-il
Details Dat file Parser  
(hq010-il) HQ 0/10 AIRFOIL
Quabeck HQ 0/10 R/C sailplane airfoil
Max thickness 10% at 33.9% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
HQ 0/10 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0011100 0.0032600
 0.0043300 0.0075500
 0.0095600 0.0116600
 0.0170000 0.0157100
 0.0265600 0.0196700
 0.0381100 0.0234600
 0.0515600 0.0270600
 0.0670000 0.0304600
 0.0842200 0.0336700
 0.1033300 0.0367300
 0.1241100 0.0396200
 0.1464400 0.0422000
 0.1703300 0.0442400
 0.1956700 0.0456500
 0.2222200 0.0469700
 0.2500000 0.0481400
 0.2788900 0.0490000
 0.3086700 0.0496400
 0.3393300 0.0500000
 0.3705600 0.0498100
 0.4024400 0.0491000
 0.4347800 0.0481200
 0.4673300 0.0469200
 0.5000000 0.0453900
 0.5326700 0.0434300
 0.5652200 0.0410600
 0.5975600 0.0383300
 0.6294400 0.0353400
 0.6606700 0.0321800
 0.6913300 0.0289600
 0.7211100 0.0258000
 0.7500000 0.0227100
 0.7777800 0.0197400
 0.8043300 0.0168900
 0.8296700 0.0142300
 0.8535600 0.0118600
 0.8758900 0.0098000
 0.8966700 0.0079600
 0.9157800 0.0062700
 0.9330000 0.0047500
 0.9484400 0.0034700
 0.9618900 0.0024500
 0.9734400 0.0016700
 0.9830000 0.0010600
 0.9904400 0.0005900
 0.9956700 0.0002600
 0.9988900 0.0000700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0011100 -.0032600
 0.0043300 -.0075500
 0.0095600 -.0116600
 0.0170000 -.0157100
 0.0265600 -.0196700
 0.0381100 -.0234600
 0.0515600 -.0270600
 0.0670000 -.0304600
 0.0842200 -.0336700
 0.1033300 -.0367300
 0.1241100 -.0396200
 0.1464400 -.0422000
 0.1703300 -.0442400
 0.1956700 -.0456500
 0.2222200 -.0469700
 0.2500000 -.0481400
 0.2788900 -.0490000
 0.3086700 -.0496400
 0.3393300 -.0500000
 0.3705600 -.0498100
 0.4024400 -.0491000
 0.4347800 -.0481200
 0.4673300 -.0469200
 0.5000000 -.0453900
 0.5326700 -.0434300
 0.5652200 -.0410600
 0.5975600 -.0383300
 0.6294400 -.0353400
 0.6606700 -.0321800
 0.6913300 -.0289600
 0.7211100 -.0258000
 0.7500000 -.0227100
 0.7777800 -.0197400
 0.8043300 -.0168900
 0.8296700 -.0142300
 0.8535600 -.0118600
 0.8758900 -.0098000
 0.8966700 -.0079600
 0.9157800 -.0062700
 0.9330000 -.0047500
 0.9484400 -.0034700
 0.9618900 -.0024500
 0.9734400 -.0016700
 0.9830000 -.0010600
 0.9904400 -.0005900
 0.9956700 -.0002600
 0.9988900 -.0000700
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 79-L-100PreviewDetails
NACA 63A010 AIRFOILPreviewDetails
RYAN BQM-34 FIREBEE WING AIRFOILPreviewDetails
RAE 102 AIRFOILPreviewDetails
NASA SC(2)-0010 AIRFOILPreviewDetails
NACA 0010PreviewDetails
RAE 101 AIRFOILPreviewDetails
RAF 27 AIRFOILPreviewDetails
E230 (9.96%)PreviewDetails
LWK 79-100PreviewDetails

Polars for HQ 0/10 AIRFOIL (hq010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hq010-il50,000928 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq010-il50,000527.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hq010-il100,000939.7 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hq010-il100,000536 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hq010-il200,000950.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hq010-il200,000541.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq010-il500,000954.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq010-il500,000556.9 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hq010-il1,000,000971 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hq010-il1,000,000570.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit