How does a Rocket Engine Nozzle Work (Part 2) - What are "Shock (or MACH) Diamonds"?
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- Опубликовано: 20 авг 2024
- #Shockwaves #MachNumber #Supersonic #Aerodynamics
Hi Everyone!
Welcome to Part 2 of my Rocket Engine Videos!
This video is MUCH more informative and covers a LOT more interesting content than Part 1.
If you missed PART 1 you can find it here at: • How does a Rocket Engi...
Have you ever seen a diamond like air pattern outside of a fighter jet afterburner or a rocket engine and wondered why that happens? These shock diamonds are typically seen in images of the SR-71 Blackbird and other supersonic aircraft. In addition, you can see these shocks in rocket engines tested at low altitudes.
These diamond like shocks are oblique shocks which form due to the over expanded conditions of the nozzle. Over expanded simply means that the pressure of the air at the exit is much lesser than the pressure outside (ambient). This causes shock waves to form to try and maintain the pressure equilibrium in the flow.
This video describes in detail, how these shocks are formed. If you are interested in jet & rocket propulsion, this video is a must see! In brief this video covers,
1) Shock Diamonds (why they form)
2) Oblique Shocks
3) Expansion
4) Nozzle Theory
5) Over Expanded Nozzles
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VDEngineering
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Hey everyone, Thanks for watching! You can find Parts 1 and 3 here at:
Part 1: ruclips.net/video/3zagXTc4hBk/видео.html&t
Part 3: ruclips.net/video/cXB09lTpVeM/видео.html
Can fuel efficiency be optimized via balancing the symmetry in shock diamond formation?
You are seriously awesome dude
Very nice explanation. Could be more elaborated with graphs along the nozzle length. God Bless.
IF WE LEAVE AEROSPIKE ENGINES TO ONE SIDE IS THERE AN IDEAL NOZZLE SHAPE FOR SEA LEVEL PERFORMANCE AND AN IDEAL NOZZLE SHAPE FOR VACUUM PERFORMANCE ? ? ?
Of all the explanations out there this is the one that is most complete. I think I understand the concept perfectly now
we know that expansion of nozzle is to increase the velocity .But in the video the explanation tells that at diverging end the velocity will decrease and pressure will increase.I have a small doubt about on this so. will u please explain it.
The explanation he’s giving is kinda wrong. It would be right that an expansion would slow the flow down and therefore increase pressure. However when the gas flow reaches over mach 1 the gas gets compressed in the throat, the nozzle expands to release pressure and therefore velocity increases
So why does oblique shock continue to form shock diamonds along the thrust vector? Does the geometry of the exhaust cause the gasses to fold back into itself?
Great work. How do you do the animations?
This is a second video from you I've watched. I like how you present everything, including your small face when you are showing your sketches.
Hey I'm from Trinidad.
I admire the tutorials you're giving
For that's the reason why I want you keep adding
It's put in a simple way in understanding
And that's a good going
New to a lot of this but really can’t get enough. Your videos are terrific and have helped me a lot. I’m currently designing tanks and an aero spike engine design, but realize to do it right I should model it first. How many choices are there for cad packages that will model rockets problems, flow rates pressures gas behavior etc?
Excellent except for... @ 3:00 exhaust velocity delta is related to cross section area decrease which only occurs in the converging nozzle section, but the graphic following was an illustration of the diverging nozzle section so... Stating the exhaust flow velocity delta wrt to increasing cross section area would be better IMO.
Great video.
Great video! Thanks for explaining this
You can explain things well. Enjoyed the video.
Thanks a lot!
A good explanation. It's a shame that shock diamonds are inefficient though because they look really cool.
I appreciate your work. Helped me a lot with my research
Really love your videos!!
Thank you.
So VD was engineered? I KNEW IT ! ! ! ! ! ! ! ! ! :P
If the diamonds are happening due to high speed travel, why do they happen even on a static jet mounted on the ground ? See video :
ruclips.net/video/UGGSFmEcoSE/видео.html
Then why havent NASA made a rocket engine that is able to change its nozzle's diverging section so it can have maximum efficiency at any alitutude/conditions?
It's not easy to make that's why
Actually, they did. You may be familiar with the aerospike. it is a masterpiece from a physics standpoint, but an engineering nightmare due to the increased cooling needs. that's why the lower stages of rockets have nozzles optimized for the atmosphere and the upper optimized for the vaccum of space.
@@mikeyslab2471
Reaction Sabre Engines - ruclips.net/video/alc8aCoDsYo/видео.html
What is that song from at the beginning m
From which college or book You got all this
Modern compressible flow, by John Anderson is one of THE books for this topic. J Anderson is a genius!
@@ibonitog Thanks!
I have one question, in amateur rocketry people recommend spinning the rocket in its own axis to stabilize it. How does actual stabilizing works? How does SpaceX for example stabilizes its rockets while ascending?
Samuel Camilo Padilla Castro try searching for gyroscopic rocket stabilization. That should yield promising results
Venereal Disease Engineering?
I really appreciate this video, I'm using it to help me in my homework.
I think you made a mistake at 2:20 since you said the pressure downstream of the normal shock was higher than the pressure upstream.