Flow dynamics at the minimum starting condition of a supersonic diffuser to simulate a rocket’s high altitude performance on the ground

Abstract

A numerical analysis was conducted to investigate and characterize the unsteadiness of the flow structure and oscillatory vacuum pressure inside of a supersonic diffuser equipped to simulate high-altitude rocket performance on the ground. A physical model including a rocket motor, vacuum chamber, and diffuser, which have axisymmetric configurations was employed. Emphasis was placed on investigating the physical phenomena of very complex and oscillatory flow evolutions in the diffuser operating very close to the starting condition, i.e. at a minimum starting condition, which is one of the major important parameters from a diffuser design point of view.

On the Assessment of Compressibility Effects of Two-Equation Turbulence Models for Supersonic Transition Flow with Flow Separation

“…The boundary condition has the same condition as the experiment. At the inlet boundary, the stagnation pressure is 50 bar (5MPa), the stagnation temperature is 300 o K, and the pressure of the outlet boundary condition is 1 atm [16,17]. Figure 13 shows the Mach number contours in the The experimental data and numerical results without compressibility correction are comparable.…”

“…Based on observations from some older Direct Numerical Simulation (DNS), Sarkar et al [6,7] postulate that the dilatation dissipation should be a function of the turbulence Mach number, Mt, defined by (16) …”

“…The four test cases are a 7% arc-bump [11,12], transonic diffuser [13,14], the supersonic impinging jet [15], and the supersonic diffuser [16,17].…”

A Numerical Analysis of Supersonic Intake Buzz in an Axisymmetric Ramjet Engine

“…In regions of low Mach number flows, however, such strong flow coupling breaks down, and the system of conservation equations becomes stiff numerically. Shih and Yang [27] proposed an algorithm based on scaling the pressure terms in the The overall numerical approach used for the current research has been validated against several supersonic flow problems [29][30][31]. …”

“…The The overall numerical approach used for the current research has been validated against several supersonic flow problems [29][30][31]. …”