Variable Cambered wing

[mklt]

I start with a NACA 0012 wing cross section. I then can magically curve the chord line to form an smooth arch around the 30% so that the leading edge is much like a droop nose and the aft magic chord forms to a 15 Deg. slope at the 66% pt and about a 30% slope at the trailing edge.

Can anyone suggest on where I might or how to calculate the Coefficients and info needed to use such wing? Do I need to develop a wind tunnel profile or can this be calculated?

 

[mohr]

Hi Mklt !!

You only need to download the designfoil demo (full functional but for 30 days)at

http://www.dreesecode.com,

then you could "deform" your NACA 0012 or another airfoil mean line.
(In this case is the chord line)

The program will calculate for you the lift/drag and moment
polar with the A of A and reynolds Number you select. Also it give to you the choice of laminar or turbulent flow. Is very easy to use.

Regards
Mohr

 

[mklt]

Thanks Mohr!

Looks like an awesome program. Did you have any thing to do with the program?

Thanks again
Mklt

 

[mohr]

Yes Mklt:

I did an airfoil performance estimation at Low Reynolds
Number because all measurements done by NACA begin with
RN= 3.000.000

I was working with small airfoil section at RN between
500.000 and 1.000.000.

To ckeck the data acquired I did comparision with some data found in a technical report, about airfoil working at low RN.The results was acceptable.
Regards

Mohr