static thrust in pounds produced by tail rotor????????

wrote in message
oups.com...
Hi
I need a perspective so this is a general question . If a 6 foot dia.
tail rotor is turning 2500 rpm how many pounds of static thrust at a
particular pitch angle would be produced????

That would depend on the chord and aerofoil section of said rototr blade.
Given all those values, it wouldn't be difficult to do the sums.

And is that for a flat
rotor blade meaning no helical twist. Any senario close to the above
would be a big help. I want to build a variable pitch rotor and need to
get an idea on the thrust output .

May I suggest a book on aerodynamic principles and mathematics? And no, I'm
not being funny, I'm being serious because without some grounding in the
basics, you're going to struggle finding answers that are simple to find
inside a calculator.

Beav

The chord and airfoil variable if in realistic proportion would have a
small effect on thrust output , but would have a huge effect on fuel
cost over the life of the craft . I was looking for a short answer to
a general question that was perhaps common knowledge in this group .
Thanks ED

wrote in message
oups.com...
The chord and airfoil variable if in realistic proportion would have a
small effect on thrust output ,

And what would you consider to be "realistic proportions"? Is a high aspect
ratio realistic, and how high is high? Is a low aspect ratio more realistic
and if so, what IS low aspect?

I was looking for a short answer to a general question that was perhaps
common knowledge in this group .

And obviously you're not interested in doing any real research.

Beav