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October 29, 2010, 02:26 |
Con-Div Nozzle Shock structure problem
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#1 |
New Member
padhu
Join Date: Jun 2009
Location: Bangalore, India
Posts: 27
Rep Power: 16 |
Dear All,
I'm working in simulation of supersonic flow through Nozzle. I need to simulate shock structure at the exit of the nozzle. My problem is, I need to simulate normal shock at the exit. for that I have calculated the exit pressure using the normal shock relation (analytically). when i am using the calculated pressure the solution diverges. I observed that the shock is found upto certain iterations, and suddenly the solution diverges. What kind of boundary conditions have to be choosen? What may be the appropriate pressure ratio suitable for this problem? In case, If I am increasing the nozzle length do i can able to capture the shock? The Simulation specifications are, Nozzle Length = 3.1 m , Throat is at 1 m from inlet, Area ratio (Aexit/A*) = 2.53, Designed Mexit = 2.53. The solver details are, density based, implicit, axi-symmetric, steady, inviscid flow. Thanks in advance, padmanathan |
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Tags |
nozzle flow, shock detection |
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