Supersonic nozzle
 

Dear CFD people:

Is it possible to obtain uniform, isentropic, shock free flow through a minimum length nozzle (MLN), (the expansion section is eliminated) ?

I believe it is possible but..

My question is: If it is possible to obtain uniform, isentropic, shock free flow through MLN, why people want to design a long supersonic nozzle with gently curved expansion section.

Any comment is appreciated

Thank you

Danny

Re: Supersonic nozzle
 

Theoretically, yes it's possible, neglecting viscous effects.

I think there are some practical issues with the expansion region. With the expansion concentrated on a single point (or curve), the wall of a MLN usually has a sharp edge, right at the throat, around which the flow accelerates from Mach 1 to the maximum Mach number.

One of the effects of viscosity could be flow separation at that edge. I am not sure if this is a big issue. It might not be, because of the acceleration.

Another problem is heat. In practice a perfectly sharp expansion edge (even if you could manufacture it) will be hard to maintain because of friction. Eventually the edge will burn off.

Anyhow, even though the exact MLN from inviscid theory may not be realistic, I am pretty sure that approximate MLNs (with very small expansion sections) are in use. How did you get the impression that this design is not used?

Re: Supersonic nozzle
 

Theoritically yes applying the 1-D isentropic relations you can define a back pressure at which the flow from the nozzle is supersonic. But in reality the effect of the boundary layer interaction plays the spoilsport.

-H

Re: Supersonic nozzle
 

To get supersonic flow, the nozzle must have a expansion section, to allow the flow the expand from sonic to supersonic. Then the expansion section have to be extended further (with careful design) to absorb the expansion waves, and finally get a "uniform" flow. The design of the expansion section is crucial to the flow quality.

If you say there's a MLN, then, yes, there should be one based on inviscid assumption.

Hope this answers your question. Pete

Re: Supersonic nozzle
 

Thank you all for the responses.

Danny

Axisymmetric Nozzle contour MOC
 

Hi,

Does anybody have a Matlab code for MOC contour design of an axisymmetric supersonic (Mach 2) nozzle they could send/sell me?

Thanks in advance,
Logan

i am searching for a code, to design supersonic nozzle .

Part of the issue is what you want to use the nozzle for. For a rocket nozzle, you want all of the gases moving the same direction (axially), to get maximum thrust. Early nozzles were conical (V-2, Redstone), and because some of the gases had a radial velocity component when leaving those nozzles, there was some degree of loss or inefficiency. If you wanted to, you could expand a gas through a simple orifice from high pressure directly to ambient, but the expansion fan at the exit will turn a great deal of the gas outward, radially, and hence, thrust is greatly reduced. To design a nozzle that directs all of the gases axially at the exit, the geometric angle of expansion at the throat can only be so large because the flow must be turned back onto itself without any shocks being generated. That takes a nozzle of finite length. Look for papers by G.V.R. Rao, who designed Rocketdyne's nozzles.

To my knowledge, the shortest nozzles ever developed are the "expansion-deflection" or "plug" nozzles. These were also developed by Rocketdyne (in fact they were even patented by Rocketdyne). Their Aerospike engine was just about as short as possible, and allowed for high efficiency even under highly off-design conditions. Pity NASA wasn't smart enough to employ those engines rather than the ones they ended up requiring for the Space Shuttle. But I digress...


Rich

coding for supersonic 3d nozzle
 

Hi,

Does anybody have a Matlab code for MOC contour design of an axisymmetric supersonic (Mach 2) nozzle they could send me @

dinesh_astronaut@yahoo.co.in

Thanks in advance,
DINESH

hello ,
I need a code to design axisymmetric supersonic nozzle if any one has it then please do send to - biradarradhe@gmail.com
Regards
D B