It does make me wonder what is going into Scampton that makes it secure? I’m not surprised at what I read in todays echo, and I’ve said on here before that I don’t think the base will close. They must have something in mind?

Seeing as Machrihanish is slated for sale maybe Scampton will become the RAF’s new “area 51”.

Without reheat it drops as airflow expends etc…

And if I tell you a gas turbine runs on a constant pressure combustion cycle, do you know the answer then?

I’m please you like it.:D

Note the mention to the increased sweep to 42* which is that of the F-22 reduced from the YF-22 48* (value for Rafale).

Same as internal combustion engine no?

Increased volume with increased temperature, this BTW is the A from the MTO ABC no?

So what does the increase in volume do in the engine?
Btw I know the formula T=M(v2-v1), but there are other permutations.

Go tell this one to the Nellis guys.:D

Read up on Mirage 2000/M53 it’s there too, BTW Inlets multi-shock configuration on Tornados doesn’t help.

It’s total dry and A-B thrust and is also much more likely to decrease with altitude and speed for the SAME type of inlets for the very same reasons, has it not been the case designers wouldn’t try to increase TETs with every new generation of engine.

Otherwise said pressure recovery depending mostly in the type of inlets you are paring them with…

RAM drag btw is (according to Nellis H-B) “the result of slowing the air from free stream to near zero speed at the inlet”.

This have another name which i believe to be Spillage drag and is the result of this recovery limit being reached.

Basicaly you’re talking about the pressure recovery limit without taking that of the engine own recovery capabilities into account nor the inlet type…

Your explaination on temps should be enough as it is self-explainatory i.e higher temperatures = higher performances at altitudes and speed (Generaly speaking thumb rule).

It’s pretty obvious that a M 53 will be able to recover a lot more of it than a RB199 at altitude (and Speed) regardless of inlets type and settings.

Depending on inlets…

Here go, you obviously didnt read my previous posts, we are not even talking about pitot intakes…

1. I’m not sure what Nellis has to do with this, they normally drop bombs there.

2. The Tornado has a variable geometry intake. I’m not sure if it still is, but it was locked in service on the GR a/c so was unable to perform it’s original function.

3. You obviously didn’t understand what I posted there. Perhaps you could explain to me what you think happens to thrust due to temperature increase, and why?

4. An awful lot was properly replied to by Schorsch, however we come back to the question of thrust increase. How does reheat increase the thrust in an engine? In your own words please.

5. Indeed, depending on inlets. That was a generalisation, you see it alot in education. Especially in the technical world, an instructer or lecturer will begin with, “in general a basic system will work as follows”. Begin with the basics.

6. I wasn’t talking specifically about pitot intakes, merely pointing out that they all have different functions.

Incidentally the first Sea harrier shot down actually had Sea Eagle testing equipment in place of where the Radar Warning Receiver should’ve been. Pilot Dave Morgan speculated in his book that this may have added to the Argentine Navy’s decision to withdraw to port. I don’t go for that myself personally, I think our submarine threat was enough.

A friend of mine was working on the Sea Eagle program at the time.
He said that when they went back to work right after Falklands had been invaded they found the missile on the floor but no a/c.:eek:

Boy please stick to playing Orange and Lemon with someone your size.

YES engine thrust generaly decreases with speed unless you use a turbojet that is, YOU wouldn’t know.:D

It would appear from this statement that you don’t know what you are talking about.
Be it ram, jet or fan, the engine will be subject to ram recovery. Typically during the first acceleration the actual thrust will decrease until ram effect kicks in which (according to my course notes) would be around 300 kts. The amount that the thrust is increased is dependant on the type of intake, the velocity of the a/c and height.

Like i said before i was not talking about the human toll on either side or humanitarian crisis. Right now in Afghanistan, the Americans are prepared to win the war at any cost, while the British are more towards a political settlement. That is all I am saying here.

I think you are the last person to ask for an informed and balanced outlook.
Perhaps you should continue this discussion at your nearest bar. I’m sure you’d find a more amenable audience.

Concorde did not need to use afterburner to break Mach 1. Had that been necessary, how could it have supercruised at Mach 2?

From what I have read, it was more fuel efficient to use afterburner to break through Mach 1 and this practice was adopted.

See post #9