# Equation of temperature increase by shock wave

1. Jan 25, 2012

【HELP】Equation of temperature increase by shock wave

Hi there!

What is the equation of the temperature increase when the ideal gas swept by a planar shock wave (Mach number, M)?

Thank you!

2. Jan 25, 2012

Re: 【HELP】Equation of temperature increase by shock wave

Another question:
If the shock wave is triggered by a piston, why it can propagate at a speed larger than that of the piston? what determine the speed of a shock?

3. Jan 25, 2012

### meldraft

Re: 【HELP】Equation of temperature increase by shock wave

I don't have my book handy to tell you the equation, but as for the second question:

The shock wave is a discontinuity in air pressure. Keep in mind that, while the shock wave is caused by your piston, the actual cause is that the air around it is moving in a certain way.

The propagation velocities are in the order of magnitude of the speed of sound. Your piston is probably moving quite slower than that. You get a shock wave because there is a discontinuity in pressure at some point around the piston.

This is the tricky part:

The piston itself is not moving faster than sound, the air at some point(s) reaches those velocities.

4. Jan 25, 2012

Re: 【HELP】Equation of temperature increase by shock wave

Thank you meldraft!

So, how to calculate the speed of a shock? is there any equations? I just what to know what exactly influence the shock speed.

BTW, I have found the temperature equation

5. Jan 25, 2012

Re: 【HELP】Equation of temperature increase by shock wave

You would do well to look up normal shock relations. They will have all the relations you are asking for and more. If you intend to do this a lot, it may be a good idea to pick up a book on compressible flow and learn where it all comes from.

6. Jan 25, 2012

Re: 【HELP】Equation of temperature increase by shock wave

Not intended to do this subject alot, just curious.

Anyway, cannot find relations between initial piston speed, and the consequent shock speed. Just know that shock propagate ahead of the piston. By how much exactly?

7. Jan 26, 2012

### meldraft

Re: 【HELP】Equation of temperature increase by shock wave

The phenomenon you are asking is very complex because, in contrast to an aircraft, the piston is moving back an forth, which means that the air flow is fully turbulent.

That being said, I imagine that the discontinuity in pressure would be caused by sudden changes in the direction of the airflow, caused by the alternating pressure between upstroke and downstroke.

For an aircraft, these are the equations:

http://www.grc.nasa.gov/WWW/k-12/airplane/normal.html

http://www.grc.nasa.gov/WWW/k-12/airplane/oblique.html

For a piston, unless you can find something in a book that I am not aware of, you would have to solve the Navier-Stokes with turbulence to see when the shock waves are formed.

A rough approximation is to consider a plane that is moving in one direction in a container where the air is moving in the other direction. If you solve the equations, you will get when the Mach number becomes greater than 1, as a function of the displacement of the piston. This value will depend on the relative velocity between the air and the piston, as well as the geometry you assume.

8. Jan 26, 2012

Re: 【HELP】Equation of temperature increase by shock wave

9. Jan 26, 2012

Re: 【HELP】Equation of temperature increase by shock wave

Turbulence has absolutely no effect in this case. The only time turbulence would have an effect is in the case of a boundary layer, and then only because you change the shape of the boundary layer. The normal and oblique shock equations are equally valid for laminar and turbulent flows except near boundaries since the normal and oblique shock relations assume inviscid flow. Then again, that means that they aren't really valid near boundaries for laminar flow either.

In general, in compressible fluid mechanics like this, the inviscid approximation is very good because (a) the flows generally involve very high Reynolds numbers, so the viscous terms are small in comparison to the rest of the terms and (b) the boundary layer is typically very thin until you start stepping into the hypersonic regime, where it can actually get very thick.

Additionally, saying things like "solve the Navier-Stokes equations with turbulence" really has no meaning. Turbulence is already built into the Navier-Stokes equations. It is fully described by them. The only difference in the Navier-Stokes equations in this case and what are traditionally used is that since this is a compressible flow, one cannot drop the bulk viscosity term as is typical. This still has nothing to do with turbulence.

10. Jan 26, 2012

### meldraft

Re: 【HELP】Equation of temperature increase by shock wave

You are saying that you can predict where the shock wave will be shaped and how it will look like, as a time dependent phenomenon, in a small closed container, and, possibly, fuel coming in, by ignoring turbulence. If this sounds right to you, I'm not one to argue I will just point out that the equations are still valid, but your field does not look like you would expect for laminar flow.

The person that manages to solve that will get a Nobel prize That is why we have turbulence models, or choose to neglect it.

Last edited: Jan 26, 2012
11. Jan 26, 2012