Thesis (Ph.D.), University of Manchester, School of Engineering.
|Contributions||University of Manchester. School of Engineering.|
|The Physical Object|
|Number of Pages||241|
Large-eddy simulation (LES) and dynamic mode decomposition (DMD) are used to study an underexpanded sonic jet injected into a supersonic crossflow and an overexpanded supersonic jet injected into a subsonic crossflow, where the flow conditions are based on the experiments of Santiago & Dutton (J. , vol. 13 (2), , pp. –) and Beresh et al. (AIAA J., vol. 43, a, Cited by: Browse All Books; Meeting Papers; Standards; Other Publications. Software/Electronic Products; Archive; Subscribe/Renew ; About; For Authors ; Vol Issue 9. No Access. Numerical Study on Turbulent Structure of Transverse Jet into Supersonic by: Numerical simulation of supersonic-supersonic shear flow mixing enhancement based on transverse jet Adding a transverse jet to the supersonic flow, the secondary eject method, is a potential method of the study of the influence of the crossflow on the supersonic flow field is as follows. Zukoski () et al.  injected gas nitrogen. Jet injection into a supersonic cross-flow is a challenging fluid dynamics problem in the field of aerospace engineering which has applications as part of a rocket thrust vector control system for noise control in cavities and fuel injection in scramjet combustion chambers. Several experimental and theoretical/numerical works have been conducted to explore this flow; however, there is a dearth.
Murrugupan and Gutmark used a high frequency actuator (HFA) with an integrated Hartmann-Springer Tube as a high frequency injector to study a pulsed supersonic jet ( to 5 kHz) injected into a supersonic crossflow. Kouchi used a high-speed valve to pulse a helium jet into a supersonic crossflow of Mach 2 at 1 kHz. Schlieren images revealed. A flat plate wind tunnel test was conducted at the Virginia Tech Supersonic wind free-stream Mach number is , the jet exit Mach number is , the unit Reynolds number is × 10 6 m − 1, and the jet pressure ratio is The jet exit is located cm downstream from the leading edge where the wind tunnel wall and the plate meet. Abstract. Transverse injection into supersonic flow is one of the most fundamental canonical flows for supersonic propulsion community, which has been studied to enhance the understanding of supersonic turbulent mixing of jet fuel and combustion in scramjet engine combustors. Gruber et al. suggest the following correlation for the penetration of the upper surface of the sonic jet in supersonic crossflow: (11) z J D = (x + a J D) where a in this equation refers to the radius of the jet exit. Later studies of hydrogen and ethylene sonic jets in supersonic crossflow in, indicate that the correlation in Eq.
In the present paper, the influence of shock wave position on sonic transverse hydrogen micro-jets in supersonic crossflow is investigated. This study focuses on mixing and shock interaction of the hydrogen jet in a Mach crossflow with various jet conditions. Flow structure and fuel/air mixing mechanism were investigated numerically. Large-eddy simulation (LES) and dynamic mode decomposition (DMD) are used to study an underexpanded sonic jet injected into a supersonic crossflow and an overexpanded supersonic jet injected into a subsonic crossflow, where the flow conditions are based on the experiments of Santiago & Dutton (J. Propul. Extensive experimental investigations have been carried out previously to study the spray structures. 6 –8 Kush and Schetz 9 used water as the liquid jet normally injected into a supersonic gas crossflow and found the liquid surface layers appear to be different in size, shape, and depth with varying jet-to-air momentum flux ratio. Gaseous jet in supersonic crossflow. Numerical study of jet injection into a supersonic crossflow. Visual observations of supersonic transverse jets. Experiments in Fluids, Vol. 14, No. 6. Flame deformation and entrainment associated with an isothermal transverse fuel jet.