On 17/08/15 10:07, Bill Sloman wrote:
> On Sunday, 16 August 2015 23:36:02 UTC+10, David Eather wrote:
>> On Sun, 16 Aug 2015 12:29:43 +1000, Bill Sloman <
bill....@gmail.com>
>> wrote:
>>> You missed the point. They use air-breathing engines so there are
>>> super-sonic shock-fronts in the combustion path.
>> No there aren't. A jet turbine is designed to specifically avoid that. The
>> speed of sound goes up with both heat an pressure
David is incorrect. Only temperature. Pressure has nothing to do with it
until you reach non-ideal gas behaviour (trans-sonic conditions).
The speed of sound is directly connected to the speed of individual
molecules. The temperature is a measure of the average kinetic energy of
those molecules bouncing off a boundary. Kinetic energy is proportional
to m*v^2; so v changes as sqrt(temp) (times a multiplier that depends on
the molecular mass and geometry).
For sea-level air, the speed of sound in m/s is almost exactly
20*sqrt(k) - where k is in degrees Kelvin.
> It has to leave the engine going backwards faster than the plane is going forwards
Bill, this is completely wrong. Any expulsion away from the direction of
travel imparts momentum.
As the space shuttle main engine approaches orbital velocity, its
exhaust is still travelling forwards at a significant multiplier. A
rocket is most efficient when the exhaust is stationary, because it
carries no waste kinetic energy (except you obviously can't launch like
that!)
Given the relatively fixed temperature limits of nozzle materials, a
rocket engine for low-speed flight needs an exhaust gas with a high
molecular mass and a low speed of sound (like the semi-burnt rubber of
the solid fuel boosters). For high-speed flight, you want a low
molecular mass and consequent high exhaust velocity - like H2O. Exactly
why the shuttle has solid fuel boosters for low-speed climb and H/LOX
engines for orbital insertion.
Clifford Heath.