Is there a maximum achievable Mach number in a convergent-divergent nozzle?

Is there a maximum achievable Mach number in a convergent-divergent nozzle?

Maximum Mach number achievable in a converging nozzle is unity. For supersonic Mach numbers, a diverging section after the throat is required. However, a diverging section alone would not guarantee a supersonic flow.

Where do we have the value of Mach number as 1 at a nozzle?

In the case of a converging nozzle, the exit of the nozzle corresponds to the nozzle throat (as seen in Figure 1); therefore, the Mach number right at the exit does not exceed 1, i.e., the flow never goes supersonic.

What is the value of the Mach number at the throat when the maximum flow rate achieves in a converging diverging nozzle?

Mach 1
The flow pattern is exactly the same as in subsonic flow, except that the flow speed at the throat has just reached Mach 1.

Does temperature affect Mach number?

So, in short – the hotter the air, the higher the Mach number, and the faster you must travel over the ground to break the sound barrier. Also – sudden changes of temperature can change the way a jet engine works, but usually that kind of problem is only caused by other jet engines.

When the Mach number is one the flow is Mcq?

Explanation: For transonic flow mach number is equal to one.

When the Mach number is increasing the temperature will?

A Mach number is a measure of airspeed, and not of ground speed. Mach is said to change when 1.0 Mach refers to different ground speeds. A sudden change of temperature will change the propulsion of a jet engine, and more importantly, it will change the way the wing reacts.

What is a convergent divergent nozzle?

This nozzle configuration is called a convergent-divergent, or CD, nozzle. In a CD nozzle, the hot exhaust leaves the combustion chamber and converges down to the minimum area, or throat, of the nozzle. The throat size is chosen to choke the flow and set the mass flow rate through the system.

How does the Mach number of a nozzle increase?

In a steady internal flow (like a nozzle) the Mach number can only reach 1 at a minimum in the cross-sectional area. When the nozzle isn’t choked, the flow through it is entirely subsonic and, if you lower the back pressure a little, the flow goes faster and the flow rate increases.

Should we use a converging or diverging nozzle for rocket engines?

Since the velocity is dropping in the diverging section, we should not use a converging-diverging nozzle; instead only use the converging nozzle for the rocket engines. However, the gas flow in a converging-diverging nozzle is not as simple as we explained in the Venturi effect.

What happens to the converging region when the nozzle is choked?

Since the exit pressure is below the choked flow exit pressure, the converging section of the nozzle does not know anything about the diverging section of the nozzle. This means that things are not changing in the converging region. Also, the mass flow passing through the nozzle is exactly equal to the case B mass flow where the flow was choked.