banned from f3

So are we to assume then that if Yoda can get chatters IP’s then so can other chatters. Doesnt sound very secure to me!

@Stripey Cat wrote:

Some good and very interesting points made by a few in here about giving about personal info – ppl are warned yet time and time they do it again.

I’m glad ppl are saying that Pilot aka Joker is not Jack – Jack is indeed sick in the head and despite what Jadey says, I do not laugh at him as I find him quite vile.

On another note, yes you can get IP addresses via the internet, but JC should be hosted on a secure server and therefore, the IP addy of the chatters on here should remain confidential.

A previous chatter called Vampy had a Guide or a Host in her pocket who told her who was who on the boards by seeing the same IP addy logging into F3.

Is similar happening again with Yoda gaining access to IP addys?

However Yoda is getting her info, the matter should be investigated and the Guide / Host banned for good, and so should Yoda.

And finally – Jadey – are you now going to apologise to Joker?

Yes, I think we should be told what tricks Yoda is up to. :shock:

cat give it a rest & go do one will u. this is all 2 heavy. chill or u will give yourself a heart attack

@yoda wrote:

pmsl I havent got any i.p addys from any hosts or guides…

Work it out its not rocket science…

note to Blossom… I’m not just another chatter.. ..I actually use me noggin.

doo doo doo doo dooooooo …I’m luvin it :D :D :D :D :D

F = lm(dot) ve + ( pe – pa ) Ae

This equation consists of two terms. The first term, called the momentum thrust, is equal to the product of the propellant mass flow rate m(dot) and the exhaust velocity ve with a correction factor l for nonaxial flow due to nozzle divergence angle. The second term is called the pressure thrust. It is equal to the difference in pressures pe and pa of the exhaust velocity and the ambient atmosphere, respectively, acting over the area Ae of the exit plane of the rocket nozzle. The combined effect of both terms is incorporated into the effective exhaust velocity c. Thus the thrust is also written

F = m(dot) c

where an average value of c is used, since it is not strictly constant.

The exhaust exit pressure is determined by the expansion ratio given by

e= Ae / At

which is the ratio of the area of the nozzle exit plane Ae and the area of the throat At . As the expansion ratio e increases, the exhaust exit pressure pe decreases.

Its typing dense boy… you can always decrease it by paying me a visit… i promise not to visit your ward afterward :wink: