Lift curve slope for NACA0012 at low Re

[aa2105]

Hi
I need a value for the 2d lift curve slope of the NACA0012. The Mach numbers I am concerned with are less than 0.1 and hence a incompressible value would suffice. The Re range is from 0 to around 275,000. Any ideas on how I can get this? Will XFOIL do it??

I have tried the Abbot and von Doenhoff book but its at Re = 3e6 or more... The ESDU datasheets dont seem to work at such low Re numbers either...

Thanks.

 

[imcjoek]

I'm no expert in this subject, but I've dabbled into radio control airplane stuff (around your Re's).

I think you will find that most polars for Re this low are of questionable accuracy as the performance of the foil will vary over a wide range even with somewhat controlled conditions.

I believe this is why you are not finding much useful data.

 

[Paul6]

I'm fairly sure you'll find what you're looking for here:

http://www.ae.uiuc.edu/m-selig/ads.html

An outstanding university group who specialize in model aircraft airfoils - 1550 of them! The data is available for sale in booklets and the data should be reliable. It's backed up by tests at the Princeton University tunnel.

Re's are usually run in steps from 60,000 to 250,000.

Paul

 

[Paul6]

The low Re data you seek is available at:

http://naca.central.cranfield.ac.uk/reports/1937/naca-report-586.pdf

Data was gathered in their variable density tunnel.

Their lowest Re is 42,000.

Lacking is any data at Re=0
I would imagine the stall characteristic there is quite nasty, altho the drag must be amazingly low.

Paul