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RE: Collecting material for a FAQ - 2/9/2006 4:57:51 PM   
mesae



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< Message edited by mesae -- 3/10/2006 3:55:31 PM >


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RE: Collecting material for a FAQ - 2/9/2006 5:52:02 PM   
mesae



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quote:

ORIGINAL: Espresso-Outfitters
...Actually, you can do plenty of real world observations in this area as long as you low tech it, ie. tape the weights on, carve some simple foam for it's entire construction, use the glue gun to attach things and see how the glide tests go with your original prototype,...



Yes I know. I have done that too.

I'm not trying to place any limits on methods of design and/or experimentation. I'm suggesting that ignoring hard-won knowledge is limiting, even when trying "new" ideas. Almost all "new" ideas really turn out to be variations on previously understood principles anyway. Sometimes new technology allows configurations that were previously impossible, such as pitch-unstable aircraft with computer stabilization.

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RE: Collecting material for a FAQ - 2/9/2006 11:14:39 PM   
Espresso-Outfitters


 

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Please keep in mind, I never threw out the book for traditional design procedures, by all means, those are the foundation of any good aircraft design and understing these by default are mandatory if you are going to be creating your own original designs, I was just trying to convey the fact that this science is still being developed and in all cases, real world flight testing is the bottom line. It gets really strange when you take a perfectly normal design that's mainstream and scale it down into smaller sizes only to find out it doesn't fly at all in those scales, yet other designs which thrive in it, do not in the larger realm. I'm digging the modern materials we have to work with, the micro receivers, powerful electrical motors and power packs, it sure beats what I was using 26 years ago. Where I drew the line is when I had others with vastly more experience then I in this field mainstream tell me something was impossible, only to ignore then, create, fly, test and find out they were wrong, I'll take the flying disc for example. Alone, by itself it is hopeless "without computer aided control", placing rudders at the proper 45 degree angle and creating a non symmetrical aerofoil does indeed allow it to fly. To expand upon this, Roy L. Clarks disc, at least one of them was the predecessor for the modern wing with all of the extra's, why it wasn't looked at more closely is beyond me, but it took many years for science to catch up to him. Davinci created a working aerofoil, the Vikings did the same with their long boat rudder, yet it took centuries to have it reinvented.

I then have to expand upon this where you have a team of highly educated, highly skilled people build a new design having to cross their fingers and/or face failures in spite of the fact that everything was calculated, so it shows me that science alone doesn't solve the equasion, it's a combination of that and thinking out of the box. What the original poster is trying to do is set up something that's universal, which is impossible, you can only say this is the general guide and fine tuning it for your particular application will require individual effort on your end to perfect it. The flying basketball will work as long as the basketball is spinning while the rest of the armature, wings, tail, etc. are stationary, the symmetrical flying disc will work without any tail assembly, again, it has to be spinning, or at least the dome and/or body needs to in order to maintain stability. I don't know all about every subtle nuance of aircraft design, just enough in my little corner and I'm developing a working set of procedures, designs and formula's that are not mainstream by any means, the old school stuff isn't the issue, that's a given throughout it all, it's implimenting it properly and expanding upon it dramatically, especially with the odd shapes is where science left me high and dry, so I opted to use the trial and error approach to fine tune things after the fundamentals were addressed.

The main formula I recently nailed down "pretty much" is the powertrain weight to wing mass ratio, everybody tells me it's about prop size and thrust, but when you are dealing with model electrics, you are limited as to what is on hand so have to work within those confines and in fact, I'm finding it easier to design starting with the hardware, weighing it prior to determining the proper scale of craft I should be building. If it were full sized units, or just wind tunnel tests, I can ignore that since the technology in those areas give you alot more options and I then have to go back to thrust and prop size.

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RE: Collecting material for a FAQ - 2/10/2006 12:22:18 PM   
mesae



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I don't disagree with any of that. I was trying, not entirely successfully, to keep to the subject of this thread by addressing (and re-addressing) a carefully identified gross error in one of the sources posted. This other discussion about various ways to approach design belongs in a different thread.

Do you have a source to post, or do you want to comment on my particular critique of one of those sources, namely the Cessna 172 tail down-force issue on the following web site which was posted earlier? http://www.av8n.com/how/

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RE: Collecting material for a FAQ - 3/16/2006 3:54:47 AM   
paradigm


 

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I have to say, (despite some of my recent posts) that there is a possibility of having a positive lift on the h. tail with a stable configuration. It's a matter of nomenclature. In order to get a positive force on the h. tail, the aerodynamic center of the wing-fuselage (without the h. tail) must be ahead of the c.g. so much so that the nose up moment created by this is larger than the aerodynamic moment of the wing-fuselage combination. (A cambered wing will almost always have a nose down pitching moment.) This means the wing-fuselage combination must be unstable.

Just for reference, there is actually a load case used for structural sizing of the horizontal tail of the Boeing 737 that has a force acting the forward direction. Tell me what kind of crazy flight condition this is.

I guess you should never say never...oh wait.

< Message edited by paradigm -- 3/16/2006 4:57:53 AM >

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RE: Collecting material for a FAQ - 3/16/2006 12:13:53 PM   
mesae



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quote:

ORIGINAL: paradigm

I have to say, (despite some of my recent posts) that there is a possibility of having a positive lift on the h. tail with a stable configuration. It's a matter of nomenclature. In order to get a positive force on the h. tail, the aerodynamic center of the wing-fuselage (without the h. tail) must be ahead of the c.g. so much so that the nose up moment created by this is larger than the aerodynamic moment of the wing-fuselage combination. (A cambered wing will almost always have a nose down pitching moment.) This means the wing-fuselage combination must be unstable.

Just for reference, there is actually a load case used for structural sizing of the horizontal tail of the Boeing 737 that has a force acting the forward direction. Tell me what kind of crazy flight condition this is.

I guess you should never say never...oh wait.



Well said. But at the risk of being repetitious, my argument is for a specific aircraft make and model, and the methods used by a particular web site author to "prove" positive tail lift under specific conditions, contrary to certain Cessna engineer's unofficial advice. Their advice was that the only way the C-172 tail would be lifting positively, is if the CG was aft of the aft limit. I constrained my objection to approved loadings.

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RE: Collecting material for a FAQ - 9/25/2006 10:09:12 PM   
Bax


 

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For basic design, you don't even need formulas. A bit of work with pencil, paper, a straightedge, and a French Curve is all you need. See my post and following in this thread:

http://www.rcuniverse.com/forum/m_4770546/tm.htm

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