Mailing List flyrotary@lancaironline.net Message #8520
From: Ed Anderson <eanderson@carolina.rr.com>
Subject: Trim Adjustment was Re: [FlyRotary] Re: engine mount geometry
Date: Sun, 23 May 2004 11:51:56 -0400
To: Rotary motors in aircraft <flyrotary@lancaironline.net>
Message
 
 I would like to hear what you guys say about this geometry.  does the vert stab offset create drag?  is one way better than another?  will higher cruise speeds affect the alignment, I know it affects rudder trim?
Kevin Lane  Portland, OR 
 
I'd like to know this as well.  As far as I can tell, offsetting the vert stab is no different than applying some rudder trim, which I can certainly do.  The real question for me is whether the engine offset is any better than rudder trim, in terms of drag at cruise speed.  
 
Cheers,
Rusty (making the TB flange, and fitting the tubes later this afternoon)   
I think this gets to be a bit of a complex aerodynamic Question.  Rudder or any trim offers some drag, however if it aligns the body of the aircraft more with the airstream, there could be an overall reduction in drag.  I would hesitate to offset the vertical stab.  Here's my reason.
 
1. Any fixed trim is generally only good for one airspeed and power setting, so unless you never intend or think your gear box, prop or engine is going to change I wouldn't try to compensate with vertical stab.  Once it set, it a lot of work to change.
 
2.  Cockpit   trim is of course the ideal, but then you may have to rig up something to drive the trim tab, worry about what that might do to flutter points, etc. this one takes time, money and effort to get it right.
 
3.  An adjustable trim (such as a rudder trim tab) can be adjusted to take care of such changes as mentioned in 1 above
 
All in all, its hard to beat a trim tab for adjustability, weight, cost, and ease of application and since a vertical stab orientation or a trim tab are both only idea for one airspeed and the tab is much easier to adjust - I would vote for it.
 
 
Just my 0.02 worth
 
Ed Anderson
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