Recent content by stephane

Thanks for your response but I ask about thé shock ahead pitot in supersonic an since thé flow is non isentropic so thé stagnation pressure is différente so thé value measured by pitot is false in supersonic régime no...?..

Hi, Please could you explain the difference between a subsonic Pitot tube and supersonic one Thanks

Hi all, I have some prob to undestand the shock wave in compressible flow, more precisely the "theta, beta, Mach curve) - Why when "theta" exceeds theta (max) there is no oblique shock? (how we can explain this physicaly)? - What is the difference betwwen weak shock and strong shock? - why in...

Mechanical or thermal energy.?

Hi all Why the entropy increase across the stock wave.? How we can explain it Thanks

Hi all, could you help me plaese to solve this problem: A supersonic airplane is traveling at an altitude of 4 (y-direction). The noise generated by the plane at point A reached the observer on the ground at point B after 20 (the distance from A to B is 5km in x-direction). Assuming isothermal...

So this is exactly my problem I can't understand how we can slow a flow adiabaticaly ? if you have a real example thanks to give it

I asked for a duct because a find an exercise like (so here we have two stagnation points?? no): Air flows adiabatically through a duct. At point 1 the velocity is 270 m/s, with T1=310 K and p1=160 kPa. At point 2 further downstream u2 =290 m/s and p2 =135 kPa. Compute, 1. stagnation...

Thanks Jack for your answer, Ok, but why we have the stagnation points in a Nozzle (duct) (stagnation point in the converging part and stagnation point in tne diverging part )??

I asked for the stagnation properties? what is the definition of stagnation properties? and why at the nose of an airfoil the velocity is zero? I can't understund the purpose of stagnation point/properties

Hi Boneh3ad, I have a question about the stagnation properties (stagnation pressure, temperature, density, etc.), normaly we have the stagnation state if the velocity equal to zero, but why we have the stagnation point in the nose of airfoil? why he velocity in the nose of airfoil equal zero...

Its OK I found the response :) :) Thank you very much

Hi, In the some Nozzle prob we did not take into account the pressure integral (pdA)? why? in some case we take this term and in others no?? there is an explanation please Thanks

Thank you a lot! So if I undestood, this term is applicable in incompressible and compressible flow? or juste compressible *

Its verry clear, So this force represents the force excerted o the throat of the nozzle? right? since the first term is the force at the inlet and the 2sd is the force at the outlet ?