25:54 Forgot to add Bartz approximation equation. You can find it here, along with lecture notes about it: ocw.mit.edu/courses/aeronautics-and-astronautics/16-512-rocket-propulsion-fall-2005/lecture-notes/lecture_7.pdf (p. 9, fig. 30)
You just tied together my fluid mechanics, propulsion, and gas dynamics courses in a way that they actually make sense together. They were all so abstract to me before, thank you so much. Also notability is the best.
FOR ANYONE READING: There is a typo in the isentropic Mach relations, p and rho equations should be to the -y/(y-1) in the video there isn't a negative sign. Great video though, very imformative
This is so stupidly fascinating, but what are prior requirements to understand this subject? I have no clue about all the maths/physics behind it, but I want to know more and more! PD: Liked and subscribed!
4:50 Lightes gas dont make sense. We want kinetic energy wich before you mention is speed*mass so if reduce mas you lose thrust. What i see is: more HYDROGEN more combustion(chimic reaction) more ISP: H2>CH4(methane)>C2H6(Ether)....>C3H7NO2S(RP1(i think is the worst because less Hydrogen per Carbon and "NO2S" is just useless weight. That make me think in NH3(Amonio but its nasty reaction and Nitrogen weght more than Carbon))
If you you double the speed of an object you quadruple the kinetic energy and if you double it’s mass you double its kinetic energy so by having a lighter gas you can have more kinetic energy because you can accelerate it faster. And you can carry more too I think
Hey mate, I have a question for you. What is more desirable regarding fuel oxidizer mixing in the chamber? That the fuel and oxidizer both comes into the chamber as gas phases, or both as liquid, or one as liquid and the other as a gas? Because I guess you would not, heat transfer wise, want the fuel to turn into fully gas(nuclear boiling ok) in the cooling jacket, but you would also not like to have a long liquid fuel penetration length in the chamber. So how would you design the engine so that you make sure the bulk average temperature of the fuel is just shy of boiling when entering the injector!? That is a hard problem I think! Also because I guess the amount of cooling mass flow of fuel is fixed, as well as the initial temperature of the fuel.
Few thoughts. I think from a mixing perspective, gaseous injection is better, but typically fuels are present in liquid form so extra steps need to be taken in order to turn them into gases. IIRC SpaceX's Raptors do gaseous injection. But I gess, liquid-liquid injectors aim for mechanical atomization rather than boiling them, so having them right below boiling point is less of a concern
I have questions about the CC. With nasa cea, i can achieve stagnition conditions with infinite area nozzle. How it can be appliciable to reality ? How can I tide the CC to nozzle ?
@@xxWender98xx and according for what I have to choose it? according a chamber material ? I mean , for example, if someone chooses 1000 psi, it means that he did choose it according the material he bought?
@@emmetray9703 You must always seek the highest pressure in order to have the maximum efficiency and thrust, so you choose it based on the material you want to use. If you want a cheap simple engine without regenerative cooling maybe you choose a lower pressure.
25:54 Forgot to add Bartz approximation equation.
You can find it here, along with lecture notes about it:
ocw.mit.edu/courses/aeronautics-and-astronautics/16-512-rocket-propulsion-fall-2005/lecture-notes/lecture_7.pdf (p. 9, fig. 30)
Heard KSP music, so now I know this guy knows his stuff…
I was thinking the same thing lmao
yes ksp music
Speaking the truths
this is actually so real
i love how the ksp music keeps playing xd
Fits the theme of the video
I heard it too lol
You just tied together my fluid mechanics, propulsion, and gas dynamics courses in a way that they actually make sense together. They were all so abstract to me before, thank you so much. Also notability is the best.
cannot have enough words to thank you for this beautiful content you have delivered to me
FOR ANYONE READING: There is a typo in the isentropic Mach relations, p and rho equations should be to the -y/(y-1) in the video there isn't a negative sign.
Great video though, very imformative
awesome content thank you
OK, I will need to watch it like 8 times
very good content
Great video
100 views, pog?
1000 views, pog?
@@makarlock Pog
10000 views? pog?
Chamber pressure is pressure created during combustion isn't right??
Is that KSP music LOL?
This is so stupidly fascinating, but what are prior requirements to understand this subject? I have no clue about all the maths/physics behind it, but I want to know more and more!
PD: Liked and subscribed!
Thermodynamics and fluid dynamics.
Ok but there are like a million different specific impulse formulas on the internet which one is true can someone help
4:50 Lightes gas dont make sense. We want kinetic energy wich before you mention is speed*mass so if reduce mas you lose thrust.
What i see is: more HYDROGEN more combustion(chimic reaction) more ISP: H2>CH4(methane)>C2H6(Ether)....>C3H7NO2S(RP1(i think is the worst because less Hydrogen per Carbon and "NO2S" is just useless weight. That make me think in NH3(Amonio but its nasty reaction and Nitrogen weght more than Carbon))
If you you double the speed of an object you quadruple the kinetic energy and if you double it’s mass you double its kinetic energy so by having a lighter gas you can have more kinetic energy because you can accelerate it faster. And you can carry more too I think
🙌🚀
wonderfull
how do you find the combustion temperature T0?
Hey mate, I have a question for you. What is more desirable regarding fuel oxidizer mixing in the chamber? That the fuel and oxidizer both comes into the chamber as gas phases, or both as liquid, or one as liquid and the other as a gas? Because I guess you would not, heat transfer wise, want the fuel to turn into fully gas(nuclear boiling ok) in the cooling jacket, but you would also not like to have a long liquid fuel penetration length in the chamber. So how would you design the engine so that you make sure the bulk average temperature of the fuel is just shy of boiling when entering the injector!? That is a hard problem I think! Also because I guess the amount of cooling mass flow of fuel is fixed, as well as the initial temperature of the fuel.
Few thoughts. I think from a mixing perspective, gaseous injection is better, but typically fuels are present in liquid form so extra steps need to be taken in order to turn them into gases. IIRC SpaceX's Raptors do gaseous injection.
But I gess, liquid-liquid injectors aim for mechanical atomization rather than boiling them, so having them right below boiling point is less of a concern
I have questions about the CC. With nasa cea, i can achieve stagnition conditions with infinite area nozzle. How it can be appliciable to reality ? How can I tide the CC to nozzle ?
No sound?
question : why i choose the o/f value that maximize T0/M , What about the highest spesific impulse?
T0/M is proportional to exhaust velocity/specific impulse, so maximized T0/M is maximized specific impulse I believe.
@@angl3_275Correct
How did you get combustion chamber pressure Po?
you choose it, it's a design parameter. Typically is fixed due to technological limits (around 250bar, but spacex increased the limiti to 300bar)
@@xxWender98xx and according for what I have to choose it? according a chamber material ? I mean , for example, if someone chooses 1000 psi, it means that he did choose it according the material he bought?
@@emmetray9703 You must always seek the highest pressure in order to have the maximum efficiency and thrust, so you choose it based on the material you want to use. If you want a cheap simple engine without regenerative cooling maybe you choose a lower pressure.
@@xxWender98xx got it , so at the end , it depends on material I want to use and engine structure. Thank you,
@@emmetray9703 yes, you are welcome
вот вроде нормальное объяснение с картинками, жаль только, что на импортном языке
Мог бы английский подтянуть
Its not rock.....hey......
U look like sykkuno lol
Lmfao I’ve cut my hair since then I swear
Pull up more such videos please!
im confused how do you get mass flow rate when calculating a star and at what point in the engine is this measured
nice haircut
Cool Vid