Nice simple explanation without getting into the weeds of rocket science. Explains why the first launch attempt for Artemis 1 was scrubbed due to the inability to cool engine #3.

the combustion chamber temperature can reach near 3000 Centigrade but not above that !

If you run oxygen through hot metal it will burn it like a oxy acetaline torch

In ablative cooling method, the only thing that should be taken care of is a throat. It should not change the size - usually the inner ring made of tungsten alloys is used. Combustion chanber will lose the inner layer (layer by layer) but the performance impact is not so severe, especially on first stages with altitude changes. Also depends on material - carbon fibers or selica fibers can sustain upto 2000 C which is enough for low performance fuels (not LOX/LH, or ACIDS and Hydrozines, and of course not a Methane). But look at the possibilities - with ablative nozzles and electrical turbopumps using low-performance propellants, the total cost of launcher can be surprisingly cheap for 1000-2000 kg to LEO payload capacity :)))) I rocket industry, efficiency costs a lot. Better to be low profile, non-efficient performance will be giving a huge launcher size to payload capacity ratio, but will be cheap, reliable and ecological. It was proven by Armstrong Siddeley in late 60-s, Beal Aerospace in late 90-s.

Thank you. your video gives good explanation of cooling methods. your video will help me in my exams.

Good video with nice graphics and explanation but the audio is not that clear which makes it a little difficult to connect. Kindly look forward to this issues in the upcoming videos. Rest good work, looking forward to see more of your videos.

Thank you, i found this very interesting!

Hey, as long as we're talking about nozzles and velocities, I'd like to hear your take on the difference between KE and Momentum (p). Now KE is proportional to V^2 and p is linear. What the heck is the difference. I mean if I go bowling and I throw the ball, what is at work knocking the pins over. I always said it was KE, but then someone said it's p. The question came up because I never ever bowl, and one time I happened to pick up a 15lb ball instead of a 16. I was able to roll the ball so much faster that pins were flying all over the place. 5 strikes in a row kind of flying. So I thought that the V^2 was why. But if it's just p, then would it have made that much of a difference? Or any difference at all? And Olaf Willcocx told me that KE in a rocket nozzle indicates that v should be as low as possible and m as high (within sane limits) so that thrust is increased and fuel consumption is minimized. Can you explain any of that?

What is area ratio in rockets

Wow

tank

What about Solid boosters ?

😝