Unsteady Transition From a Mach to a Regular Shockwave Intersection | Zendy

S. J. Karabelas | Zendy; N.C. Markatos | Zendy

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Unsteady Transition From a Mach to a Regular Shockwave Intersection

Author(s) -

S. J. Karabelas,

N.C. Markatos

Publication year - 2021

Publication title -

wseas transactions on heat and mass transfer

Language(s) - English

Resource type - Journals

eISSN - 2224-3461

pISSN - 1790-5044

DOI - 10.37394/232012.2021.16.18

Subject(s) - mach number , mach wave , mechanics , supersonic speed , mach reflection , nozzle , drag divergence mach number , choked flow , physics , intersection (aeronautics) , classical mechanics , transonic , aerospace engineering , aerodynamics , engineering

The purpose of this research work is to perform accurate numerical computations of supersonic flow in a converging nozzle and specifically to study Mach-disks. The latter process has been widely studied over the last years. In the present study numerical simulations are performed for transient supersonic flow, tracing the transition from a Mach reflection to a regular one. This has been done by enforcing the walls of a converging nozzle to come closer together, changing the deflection angle with time. Viscosity was taken into account and the full Navier- Stokes have been solved. The results obtained clearly show the gradual extinction of the Mach disk and the eventual wave intersection to a single point

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