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Variable Cambered wing
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Source：Internet Author：Unknow Pubdate：2008-04-03
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mklt (Mechanical)
2 May 03 14:40
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 (Aeronautics)
4 May 03 0:20
Hi Mklt !!
You only need to download the designfoil demo (full functional but for 30 days)at 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 字串4
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 (Mechanical)
4 May 03 21:42
Thanks Mohr!
Looks like an awesome program. Did you have any thing to do with the program?
Thanks again
Mklt
mohr (Aeronautics)
5 May 03 3:39
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
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