Can you do a video on hybrid rockets, there aren't many on RUclips but your tutorials and videos are really helpful and informative and learn a lot about Aerospace concepts. You also make complex concepts understandable.
Thank you for the thorough explanation. Helped me greatly on a project I am working on. I had a query as to why the interface between the nozzle and the environment at 3:27, which you later call region 3, is not a wall condition. Also, how would you simulate the movement of the nozzle for instance while 3D printing? I thought of making a moving wall condition in the environment and keeping the nozzle wall constant, do you think that might work?
great work and easy explanation. thank u. but can you show some 3d meshing examples for say like "supersonic flow over a cone". there are no videos on 3d meshing on ur channel. please!!!
@@VDEngineering pls. make one more video for 2D airfoil simulation. i have done as per you showed the structured mesh, but the mesh quality in mesh metric not coming near to 1. And the results of cl/cd are not validating with the given experimental data. (I am doing airfoil cl, cd analysis of CLARK Y airfoil at Re = 500,000 , chord length = 25cm)
Can you mesh a 3 dimensional convergent nozzle which is having domain behind it.I am looking for acoustic analysis of this kind of nozzle.Thank you for your previos videos.
Could you tell me where the hottest area of a rocket flame is? Is it closest to the nozzle or out at the tip of the flames? Asking before I start an experiment.
hi sir. I want to ask a question. if there are two compressible fluids flow in the same flow area but at different speed. why the higher velocity flow has a lower static pressure?. is it same as the incompressible flow caused by the dynamic pressure? thanks
It practically makes sense that as things go faster pressure decreases. Fill a balloon with air. It's under pressure and zero speed. When the balloon bursts the air shoots out and pressure becomes zero.
I watched your vid how does a rocket engine nozzle work part one. I'm trying to determine the velocity of gas exiting under zero atmosphere. Can you give an estimate or 'ball park' figure say on average most rocket engine exhaust velocity falls between this (X mph) and this (Y mph)? Please :-D
So the flow in the divergent nozzle is faster than in the throat because properties of compressible fluids make it so. The velocity in the throat is 'sonic'? So exiting the nozzle is super sonic? Is 'sonic' the speed of sound within the compressible fluid if there is no atmosphere? Then Mach would vary with density as it passes through the nozzle?
Thank you very much. I really needed this tutorial
Great work 😊
Can you do a video on hybrid rockets, there aren't many on RUclips but your tutorials and videos are really helpful and informative and learn a lot about Aerospace concepts. You also make complex concepts understandable.
Thank you for the thorough explanation. Helped me greatly on a project I am working on. I had a query as to why the interface between the nozzle and the environment at 3:27, which you later call region 3, is not a wall condition. Also, how would you simulate the movement of the nozzle for instance while 3D printing? I thought of making a moving wall condition in the environment and keeping the nozzle wall constant, do you think that might work?
great work and easy explanation. thank u. but can you show some 3d meshing examples for say like "supersonic flow over a cone". there are no videos on 3d meshing on ur channel. please!!!
I don't think my computer can handle it, I'll try however.
@@VDEngineering pls. make one more video for 2D airfoil simulation. i have done as per you showed the structured mesh, but the mesh quality in mesh metric not coming near to 1. And the results of cl/cd are not validating with the given experimental data. (I am doing airfoil cl, cd analysis of CLARK Y airfoil at Re = 500,000 , chord length = 25cm)
Stay safe man hello from India.
Can you mesh a 3 dimensional convergent nozzle which is having domain behind it.I am looking for acoustic analysis of this kind of nozzle.Thank you for your previos videos.
Hello sir. Could you make a video on uniform meshing and inflation at the boundaries of a 2d lid driven cavity?
Hello, Do you have any hypersonic flow analysis video or script? Thanks
Could you tell me where the hottest area of a rocket flame is? Is it closest to the nozzle or out at the tip of the flames? Asking before I start an experiment.
hi sir. I want to ask a question.
if there are two compressible fluids flow in the same flow area but at different speed. why the higher velocity flow has a lower static pressure?. is it same as the incompressible flow caused by the dynamic pressure?
thanks
It practically makes sense that as things go faster pressure decreases. Fill a balloon with air. It's under pressure and zero speed. When the balloon bursts the air shoots out and pressure becomes zero.
I watched your vid how does a rocket engine nozzle work part one. I'm trying to determine the velocity of gas exiting under zero atmosphere. Can you give an estimate or 'ball park' figure say on average most rocket engine exhaust velocity falls between this (X mph) and this (Y mph)?
Please
:-D
I'm not an engineering student. Just a curious old man
So the flow in the divergent nozzle is faster than in the throat because properties of compressible fluids make it so. The velocity in the throat is 'sonic'? So exiting the nozzle is super sonic? Is 'sonic' the speed of sound within the compressible fluid if there is no atmosphere? Then Mach would vary with density as it passes through the nozzle?
can you give your e mail please?