Open AccessUnsteady 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