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« on: January 24, 2011, 07:29:57 AM »
azhaguvel
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I want a airfoil design for a trainer. Can some one give a airfoil template so that i can just print & cut it out.
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« Reply #1 on: January 24, 2011, 09:39:35 AM »
sandeepm
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I have used PROFILI, a free download air foil program. it is good but limited functionality.

http://www.aerodesign.de/

Sandeep
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« Reply #2 on: January 24, 2011, 01:59:02 PM »
azhaguvel
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Thanks sandeep.
I am begginer so can you tell me the relation between chord length & wing span. Is there is one Smiley?
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« Reply #3 on: January 24, 2011, 02:13:41 PM »
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Suggest you do a search on Clark Y.....you may also want to do some basic reading on airfoils.

good luck!
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« Reply #4 on: January 24, 2011, 02:21:02 PM »
dileepbalan
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Like Anwar bhai always suggests, search the same here first.  Wink
http://www.rcindia.org/electric-planes/wing-span-and-fuse-length/

Regards,
Dileep
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« Reply #5 on: January 24, 2011, 02:37:12 PM »
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 since I am online, thought I'd just add a few points for Sandeep to elaborate later on.

 In simple terms, the relation between span and chord  is known as aspect ratio.

 Typically, a trainer's chord is 1/6th of its span. For example, a trainer with span of 36 in should have a chord of 6 in. However, if you wish to make a glider with a wing of the same span, then the chord should be 1/9th of the span, or 4in.

 Thickness of the airfoil is also important depending on the application.

 However, for the time being lets consider the following Example that you can follow if you wish:

1. Span - 48 in.
2. Chord - 48/6=8 in
3. Thickness of the airfoil - 8 to 12 % of the chord
     
    This means, the thickest point of the airfoil* should measure anywhere between 8 to 12% of the chord. So for a chord of 8 in, the thickness could vary between 1 to .66 in ( or 2.54cm to 1.67cm). I'd recommend 1 in at least.

 * The location of the thickest point of the airfoil is usually 1/3 the distance from the leading edge of the wing. In this example, that would be 2.66 in from the LE.

** The range of the thickness can vary beyond 8-12%. A thicker airfoil is slower, creates more lift and hence most suited for trainers.

 You can also go to http://www.ae.illinois.edu/m-selig/ads/coord_database.html 
and click any of the alphabets - this would open up a series of airfoils.

 But there's a lot you can read on the net.... Thumbs Up



   
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« Reply #6 on: January 24, 2011, 04:32:52 PM »
azhaguvel
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Nice to see more people coming for help.  Grin

chord is the distance between leading edge & trailing edge.
Wing span is distance between two wing tips.

airfoil.jpg
Re: Airfoil for trainer
* airfoil.jpg (15.42 KB, 480x266 - viewed 2874 times.)
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« Reply #7 on: January 24, 2011, 05:16:54 PM »
azhaguvel
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Awesome explaination  Clap Clap Clap Bow Bow Bow

thanks bmblb.
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« Reply #8 on: January 24, 2011, 07:35:54 PM »
azhaguvel
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Like wise is there a dimension for

1. The vertical & horizontal stabilizer which should be there for a particular airfoil (chord length, wing span & thickness of airfoil).

2. Fuselage length from the wing to the point where it has vertical & horizontal stabilizer?
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« Reply #9 on: January 24, 2011, 07:54:23 PM »
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U can find an article as how to design ur own spad in spadworld.net forum..In tat each n every relationship is explained..
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« Reply #10 on: January 24, 2011, 11:05:22 PM »
azhaguvel
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I got a software from this link
http://www.grc.nasa.gov/WWW/k-12/FoilSim/index.html
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« Reply #11 on: January 28, 2011, 12:13:53 PM »
azhaguvel
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I am planning to build a pusher

wing span - 100cm
chord length -100/7.6=> 13cm

I made the chord length so that the plane has good gliding capability.
I am using clark-Y design as bmblb suggested.

Is this ok?
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« Reply #12 on: January 28, 2011, 12:14:26 PM »
azhaguvel
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Clark y design

Clark_y.jpg
Re: Airfoil for trainer
* Clark_y.jpg (10.48 KB, 800x208 - viewed 4626 times.)
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« Reply #13 on: January 28, 2011, 01:51:32 PM »
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Like wise is there a dimension for

1. The vertical & horizontal stabilizer which should be there for a particular airfoil (chord length, wing span & thickness of airfoil).

The area of the vertical stab is usually 7-10% that of the wing and the horizontal stab is in the range of 15-20%. Suggest you draw simple forms which give you the approximate area and then make some changes to get the shape of your choice, without majorly altering the area. Plan for healthy size since its a trainer.

2. Fuselage length from the wing to the point where it has vertical & horizontal stabilizer?

As regards the length of the fuse, I follow this:

Wing Span/Fuselage=1.8

Fuselage=wingspan/1.8 (For example, for a wingspan of 48in, the fuselage can be anywhere from 27 to 33 in.
The Distance between the TE of the wing to the LE of the horizontal stab is the tricky one and can make considerable difference in the performance of your plane.

Start with this for the Fuse:

1. Nose to LE of Wing = 1 chord length
2. LE to TE of Wing = Chord length itself.
3. TE of Wing to LE of Hoz Stab = 1.5 to 2 times chord.

This is a crude way but will do. You may have some challenges with getting your CG at the right place.....but that is best experienced and you will eventually get it.

share pics of your plane as your progress....
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« Reply #14 on: January 28, 2011, 01:55:42 PM »
sahilkit
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i think simplex airfoil is a good place to start with  Smiley
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« Reply #15 on: January 28, 2011, 03:34:04 PM »
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azhaguvel, i agree with sahil, if your chord is going to be small, then you cant risk high cambered aerofoil, reason is,  cambered aerofoil has large CP (Centre of pressure, a point at which all lifting force is said to act) movement, problems are two fold (a) you need to balance CG perfectly(which means you have very little error margin on assessing length of the aircraft) at no stage CP can go ahead CG, you will loose control. (b) stall and recovery will be an issue, high elevator throw and frequent trimming will be required.

Bhavesh's Thumb rule is bang on, for a Clark Y ?, can be tricky.

Clark Y ? think about it, for a 1M aircraft it is little too cambered.

all the best Thumbs Up

PS
I had a little hand in the NASA Foilsim, way back in 1999, if you can crack the java class file, should find my name there in one of the comments, i guess.
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« Reply #16 on: January 28, 2011, 04:35:53 PM »
azhaguvel
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A pic of any recommended airfoil would be a great help Smiley
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« Reply #17 on: January 28, 2011, 05:38:37 PM »
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I am not generalizing, however most scratch builders start with Kline Fogleman first, it was a sensation in 1974, easy build, no movement of CP. very forgiving in design inadequacies and inaccuracies, attaching image. choose your pick. if KFm appeals to you, i can send you some reading material as well (Indicate whether you need tech or non tech stuff) Thumbs Up

KFm4.jpg
Re: Airfoil for trainer
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« Reply #18 on: January 28, 2011, 08:26:02 PM »
sahilkit
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http://www.rcgroups.com/forums/showthread.php?t=369658

try the above link, there is a program that will generate simplex airfoil will try to post a direct link

sahil
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« Reply #19 on: January 28, 2011, 08:34:45 PM »
sahilkit
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try these programs  Smiley

 http://www.hippocketaeronautics.com/hpa_plans/categories.php?cat_id=59&sessionid=4688e71830344dbc5a6007c111ed0320
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« Reply #20 on: January 28, 2011, 10:36:54 PM »
azhaguvel
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Thanks sahil & augustinev will check out your informations
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« Reply #21 on: February 03, 2011, 01:11:05 PM »
AEROVISHWA
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sir

i think this might help.....

http://adamone.rchomepage.com/cg_calc.htm

 Head Scratching

http://adamone.rchomepage.com/index5.htm
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« Reply #22 on: February 16, 2011, 01:31:36 PM »
ved
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Hi Guys
 a simple Question
 How to make a airfoil on a thermocol without using a hot wire foam cutter.
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« Reply #23 on: February 16, 2011, 02:38:49 PM »
azhaguvel
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first thing is, can a thermocol be used for a wing? its very fragile & will break right?
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« Reply #24 on: February 16, 2011, 03:38:17 PM »
ved
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Yes.
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