How Do You Calculate Stagnation Pressure in a Converging Diverging Nozzle?

[sarahqwert]

Homework Statement

a converging diverging nozzle is operating at sea level, it will be mounted on a glider that flies 26.8m/s. The entrance area is 1 m^2.

Homework Equations

what is the stagnation pressure and mach number of flow entering the nozzle? what should be throat and exit area if exit mach number is 2?
3.

at entrance M=V/a = 26.8/346 = .077
so P/P0 =.669
we are not given P so how do we find P0?

 

[I like Serena]

Homework Statement

a converging diverging nozzle is operating at sea level, it will be mounted on a glider that flies 26.8m/s. The entrance area is 1 m^2.

Homework Equations

what is the stagnation pressure and mach number of flow entering the nozzle? what should be throat and exit area if exit mach number is 2?
3.

at entrance M=V/a = 26.8/346 = .077
so P/P0 =.669
we are not given P so how do we find P0?

Hi Sarahqwert, welcome to PF!

I'm not quite sure I get all your specifications, but I think I can say that P0 is not something you need to calculate, it's usually just the "standard pressure" of 100 kPa.

Cheers!