Oblique shocks and expansion fans [Aerodynamics #19]

[@nicollelucena9152]

Thank you so much for this playlist, Prof. Van Buren. It really helped me.

[@prof.vanburen]

Glad you liked it!

[@evangelinblessyhknzrypjimp4972]

Thank you so much sir for these wonderful lectures...please keep on posting such kind of videos

[@prof.vanburen]

I'm glad you like them! I will definitely

[@ED-zp3wu]

Theses videos are THE BESTTTT

[@prof.vanburen]

Aw thanks!

[@59vijaiyaaravindthsr39]

thank you Prof.GOD!

[@prof.vanburen]

haha I'm glad you enjoyed it

[@59vijaiyaaravindthsr39]

​@@prof.vanburen yes 100% .whlle studying the working of Cd nozzle i came across a doubt. at second critical pressure when normal shock is at the end of the Cd nozzle the exit pressure which is the downstream pressure of the normal shock and at third critical pressure at which the normal shock has completely gone away form the CD nozzle so between second and third critical pressure there is a sudden huge drop in exit pressure (is my understanding right Prof?)

[@59vijaiyaaravindthsr39]

hi sir, in rayleigh flow,during addiion of heat why should the static temperature drops to increase the velocity in high subsonic speed (above M = 0.845) till Mach 1 ? and how does cooling of supersonic flow results in increse of velocity sir??

[@59vijaiyaaravindthsr39]

i can understand the process by looking at the enthalpy specific volume graph, but i cant understand the fundamentals sir

[@tom_winguill]

16:48 Even when the flow is non-isentropic, like in the case of normal and oblique shocks we considered the stagnation temperature to be the same (while deriving the Prandtl relation). What is the advantage we are getting that you have mentioned here

[@prof.vanburen]

And the stagnation pressure? From what I am seeing, it is a quantity that assumes being brought to rest isentropically.

[@engineers_hub]

Thank you, Sir!

[@prof.vanburen]

You're welcome!

[@seridiscover-101]

We really need for this course 11:01 (propulsion systems) 🙌

[@prof.vanburen]

Propulsion systems was one of my favorite undergrad courses!

[@ahmadal-areeqy9881]

@@prof.vanburen it’s absolutely interesting actually i am gonna take it next semester as i am studying aeronautical engineering so it would be so awesome if u do such these great videos for the propulsion system

[@gloxe1282]

Again, Thank you for the video Prof.Van Buren. I have a question regarding compression lift, is it possible to make a connection from it to the types of shock like in the section that starts at 18:27 and the shock expansion theory? Thank you so much Professor!

[@prof.vanburen]

I think so! Shock expansion theory seems to be just a consideration of a system of shocks and the resulting flow properties due to those shocks---this leads to subsequent forces on the object. So inherently, these forces are connected to the types of shock in the system.

[@kushmandey6880]

Thank you very much for your lectures. I was making notes for my end semester test from here. Can you please confirm if this playlist ends here???

[@prof.vanburen]

For now, yes this is the conclusion. It is where a typical undergrad aero course would end. Over the summer or in the fall---after I wrap up the fluid dynamics series---I hope to add a few videos to this one. Topics include: hypersonics, ground vehicle aerodynamics, sports aerodynamics, and rotating systems (wind turbines, lift-based thrust, etc.)

[@tom_winguill]

please make a course on aero design

[@prof.vanburen]

Haha maybe! I'm not sure I have the know-how

[@wonderfulcat7362]

Thanks a lot, Prof. Van Burren! Really nice playlist. It helped me a lot! Is the OneNote files, or their pdfs, available online anywhere for reference?

[@prof.vanburen]

Glad you liked it! I will upload a PDF of all my notes to my website in the next few days. Could you send me an email at [e-mail] so I can remember to let you know once they're ready?

[@wonderfulcat7362]

@@prof.vanburen Done! I have sent an email.

[@Kamnarautela89637]

Superb explanation ✨ But bhut chota likhte ho 😅

[@prof.vanburen]

Thank you!