Sharif Digital Repository

In this work, ignition process in a turbulent shear-less methane-air mixing layer is numerically investigated. A compressible large eddy simulation method with Smagorinsky sub-grid scale model is used to solve the flow field. Also, a thickened flame combustion model and DRM-19 reduced mechanism are used to compute species distribution and the heat release. Non-reacting mean and RMS axial velocity profiles and mean mixture fraction are validated against experimental data. Instantaneous mixture fraction contours show that the large bursts penetrate from the fuel stream into that of the oxidizer and vice versa and a random behaviour in the cross-stream direction. Flame kernel initiation, growth... 

Ignition process in a premixed methane-air swirl configuration is studied using a large eddy simulation method with Smagorinsky sub-grid scale model. A developed thickened flame combustion approach with two-step methane-air mechanism is used. Non-reacting mean and RMS axial, tangential and radial velocity profiles are validated against the experimental results. It is shown that the flow field consists of four zones: Inner Recirculation Zone, Inner Shear Layer, Outer Shear Layer and Corner Recirculation Zone. The mean and RMS of velocities and temperature in reacting flow are then validated against the experimental data. Large eddy simulation is used to investigate the ignition sequence by... 

The comparison of aerodynamic characteristics of circular and noncircular bodies using computational-fluid-dynamics (CFD) code and semi-emperical code was discussed. It was observed that the performance of aerodynamic coefficients was better for squared section body at different angles of attack. It was also observed from the study of the flow physics that the pressure difference between the front and back of the body that produce pressure drag was more in the circular body. Results show that the friction drag is more for the square body than the circular body as the surface area of the square body is large  

The flow on a section of NACA 641-412 airfoil with right and inverse triangle shaped damage was numerically investigated. The flow through the damage was driven by the pressure differential between the upper and lower wing surfaces. The results showed that for both damage shapes the flows could be categorized as weak, transitional or strong jets. For both damage cases the jet exited from the rear of the damage and its size was determined by the width of the rear part of the hole. Generally, when compared with an undamaged model, increasing incidence for a damaged model resulted in increased loss of lift coefficient, increased drag coefficient and more negative pitching moment coefficient.... 

A series of low-speed wind tunnel tests were performed to investigate the unsteady pressure distribution over an airfoil. Dynamic pitching motion was produced by oscillating the model over a range of reduced frequencies, k=0.022 - 0.066. In addition, steady data were acquired and examined to furnish as a baseline for analysis and comparison. The model was oscillated between 0-18° angle of attack. Surface static pressure was measured from x/c=5-80% for both upper and lower surfaces. The pressure coefficients in the low angle of attack range showed little overshoot when compared with the static values, while for the large angle of attack cases the differences were significant. For a constant...