Normal Shock Example Problem

[@MillionFoul]

These compressible flow video are awesome, I've been quickly using them to review stuff before the final and they've actually made my understanding better in only a few minutes.

[@turkishdiscomachine]

first time I saw somebody explain aero problems who is not indian

[@abdulkadirelmal9375]

fast and clear, great!

[@JoshTheEngineer]

Thank you!

[@williamdonaldson7111]

I'm in Aerosapce Engineering, having a hard time wrapping my head around these shock wave formulas. How do they take into account an aerodynamic or bluff body, for example? Say if we needed to calculate those ratios at different stations around an airplane fuselage, in an engine with an aerospike, a hyperloop train, etc?

[@balkrishanmahabir7982]

Very useful information

[@JoshTheEngineer]

Thanks!

[@antonomalley2367]

How do we know if it's a function of M1 or M2 (around 3:25). I've never understood that, especially if it's something like P2/P1? Does it matter static/static or static/stagnation?

[@dsdy1205]

As I understand it the way he formulated it, any ratio involving upstream and downstream properties is a function of M1, where as the P2/P02 term is comparing 2 downstream properties so is calculated as a function of M2

[@cowmos9276]

Thank you

[@JoshTheEngineer]

You're welcome!

[@rolandjosephquitola1413]

Consider a NSW with a downstream-upstream temperature ratio of 3.5 what is the mach number upstream and downstream of the shock? Show your solution.

[@rolandjosephquitola1413]

2. The flow just upstream of a NSW is at SSLC and the mach number downstream is 0.6152 determine the pressure, temperature, density, velocity, and the total pressure and temperature. Show your solution 3. The mach number behind of a NSW is 0.4752 What is the mach number in front of the wave and the pressure ratio across the shock? Show your solution.