วีดีโอ

Nobody ever talk about what happens if Throat Mach Number is larger than 1, e.g. 1.05. Surely it is not possible to hit Mach 1 right on the head, so I suggest you would rather want to be slightly higher, as lower will make your engine not work?

I compared (equation at 4:12) with ("The linear velocity of the exiting exhaust gases" in en.wikipedia.org/wiki/Rocket_engine_nozzle). Do you mean "R bar" is the universal gas constant? (at 4:27)

How does this change with monoprop or thermal engines with LOX variability? I assume then the sizing characteristic graph for optimumal ratios for fuel and oxider shift as it becomes less efficient to use oxider to raise temperature as you increase atomic mass.

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

OK, I will need to watch it like 8 times

Is that KSP music LOL?

Is there a contact address or e-mail where I can reach you? I would like to talk about the approximate temperature in Kelvin you reach in your rocket and what kind of flowmeter you prefer to control the liquid flow in this rocket.

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

PyraLink Aerospace

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.

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!

Its not rock.....hey......

Where did you post the test results please? Great test, congratulations!

Pull up more such videos please!

This is called "gas burner", not rocket engine, chaps. Back to drawing board and learn some physics :)

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))

8:01 You are wrong on that. Otherwise you have molecule wich dont generate presure inside the chamer. The problem is the temperature. if you solve that you got the best Isp.

7:25 Thanks, i dont know about this. RP-1/LOX what ratio is for stoichiometric? to see the efect on diferent presurechamber.

24:02 i like that in any stage the user can shutdown it.

look nice let see what i can learn.

have you considered machining precision pins to help perfectly line up the flanges so the pintor injector is axial my flush?

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.

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 ?

question : why i choose the o/f value that maximize T0/M , What about the highest spesific impulse?

No sound?

awesome content thank you

cannot have enough words to thank you for this beautiful content you have delivered to me

Heard KSP music, so now I know this guy knows his stuff…

<3

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вот вроде нормальное объяснение с картинками, жаль только, что на импортном языке

awesome!

Where's your testing site?

how do you find the combustion temperature T0?

Is this a test of the injector nozzles?

it is quite interesting, how can I join your group? what are the requirements?

Looks awesome, is there any numbers on the engine yet from testing? (thrust, Isp, O/F ratio)

Hello! I'm russian design and analysis engineer of liquid rocket engines. I'v 1 year experience in Energomash and 6 months experience in United Engine Corporation. I'm political refugee. And now I'm in the US. Do you know if is possible work in the US being engineer with russian degree and experience after granted for asylum?

Chamber pressure is pressure created during combustion isn't right??

So whats your tank pressure??

Very nice. can you make a video to explain about the inlet pressure? I did saw your video about the introduction to rocket engine design. I'm very interested in build a own project. I dont want to use pressurized tanks because i think this is not scalable to a real vehicle. My objective is to use a eletric pump but i dont know the necessary pressure.

very good content

Bro this channel is so cool. Keep making rocket videos.

i love how the ksp music keeps playing xd

wonderfull

beautiful

How did you get combustion chamber pressure Po?

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