A aviation & planes forum. AviationBanter

If this is your first visit, be sure to check out the FAQ by clicking the link above. You may have to register before you can post: click the register link above to proceed. To start viewing messages, select the forum that you want to visit from the selection below.

Go Back   Home » AviationBanter forum » rec.aviation newsgroups » Home Built
Site Map Home Register Authors List Search Today's Posts Mark Forums Read Web Partners

LSA specs



 
 
Thread Tools Display Modes
  #1  
Old September 25th 06, 03:57 AM posted to rec.aviation.homebuilt
J.Kahn
external usenet poster
 
Posts: 120
Default LSA specs

Peter Dohm wrote:
"J.Kahn" wrote in message
...
ET wrote:
wrote in
ups.com:

John,
I hear what you're saying, but with all that's been said here, and
investigated via spreadsheets, etc., I still don't think the Sonex can
stall near the LSA requirement at max gross wt. and no flaps which
means it is not LSA qualified. And just for grins, I looked up the
figures for the CT Flight Design ( which is a popular seller ) and
guess what. IT doesn't meet the LSA criteria. And I also looked up
the new Vans RV-12 "LSA" and you guessed it....IT doesn't meet the
stall speed criteria ( at least not on paper...I don't think it has
flown yet.) So I'm convinced that something is amiss. I'll keep
researching.

Neal

Well then guess what, the spreadsheet is what's flawed. I guarantee CT
(the best selling LSA by far) and Vans, and the Pete Buck know what they
are doing far better then the developer of your spreadsheet...

3 real world examples of planes that clearly meet the LSA specs but do

not
meet it "on paper".

Do it for the SportStar (
http://www.evektoramerica.com/sportstar.html)
and
the StingSport (http://www.sting.aero/) while your at it... I bet you

all
the money in my pocket they won't "compute" either, and the spreadsheet

is
flawed.

Forget about spread sheets. The simple formula in my earlier post...

Sea Level Stall in Kts = Sq root of: [(295 x Gr Wt) Divided by (Clmax x
Wing Area)]

Multiply by 1.15 for mph.

Assume 1.6 for the Clmax. Almost all airfoils are between 1.5 and 1.7,
which gives a 1 mph or so variation up or down relative to 1.6.

...works like a charm. I used it on the Sting sport and sure enough it
comes out to 44kts just as advertised.

Use it on the Sonex and you get 45 kts. Different airfoils will
increase or decrease that by about 1kt.

John


And the old graphs in the Dover Edition of Theory of Wing Sections look like
a CLmax of a little more than 1.6 can be achieved--plus whatever the
fuselage shape might ad.

Don't get me wrong. At 6'1" and 200#, I don't fit in the plane; and I
really don't like it anyway. I just don't have a problem with the specs;
and there have been plenty of designs over the years for which I do have a
problem with the specs.

Peter



Yeah I'm 6' and 200 and the Sonex was a very tight fit. At Osh I
commented on the lack of head room for a long torso type like me and he
said "sit in the middle". Yeah right.
 




Thread Tools
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

vB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Forum Jump

Similar Threads
Thread Thread Starter Forum Replies Last Post
ICOM A23 Transformer Specs [email protected] General Aviation 10 April 17th 06 01:32 AM
ICOM A23 Transformer Specs [email protected] Piloting 5 April 16th 06 04:23 AM
A380 spec's G. Sylvester Piloting 30 January 21st 05 10:12 AM
A36 Bonanza Specs Anthony Acri Simulators 1 December 4th 04 12:55 PM
Specs for a B24D Liberator John T. Slodyczka Military Aviation 0 November 21st 03 02:18 AM


All times are GMT +1. The time now is 03:41 AM.


Powered by vBulletin® Version 3.6.4
Copyright ©2000 - 2025, Jelsoft Enterprises Ltd.
Copyright ©2004-2025 AviationBanter.
The comments are property of their posters.