The body may be at rest in a moving fluid mountains, islands, skyscrapers, ocean platforms, flagpoles, bridge towers, pylons, trees, mussels. The fluid motion may be internal, involving transport processes internal combustion engines, cooling and ventilation systems, flows in the blood vessels and lungs.
The scales can be very large planetary scale motions — atmospheric and ocean circulations on earth, turbulence on galactic scales , or very small circulation and transport in micromachines, bubble and particle motions.
In many practical applications, a very large range of scales spanning many orders of magnitude are simultaneously present. The cylindrical fuselage and moderately swept wings of older airplanes is quickly being replaced by a wide array of blended wing-body, joined- wing, vertical take-off and land, hypersonic scamjets, and even flapping wing vehicle designs.
The growth and success of unmanned aerial vehicles UAVs and the critical need for highly fuel-efficient and environmentally responsible systems are leading to substantial innovation in aerospace configurations. The AE AFM program advances prediction and control of fluid mechanics as a means of developing highly capable, efficient, and safe aircraft, launch and reentry vehicles, rotorcraft, novel UAV configurations, and wind energy systems.
This work is of critical importance to the commercial aerospace industry, government agencies e. The AFM group has access to state of the art facilities for both experimental and computational research. The experimental facilities include the John J. Harper Wind Tunnel , located in the basement of the Guggenheim building. The primary objective of this work is to develop high-fidelity simulation model for jet noise control predictions and quantify the sound reduction when an external source frequency mode excitation is imposed on the jet flow.
Whereas passive approaches using mixing devices, such as chevrons, have been shown to reduce low-frequency noise in jet engines, such approaches incur a performance penalty since they result in a reduced thrust.
To avoid a performance penalty in reducing jet noise, the current work investigates a open-loop active noise control ANC system that utilizes a unsteady microjet actuator on the nozzle lip in the downstream The primary intent of this research was to investigate and develop a method to extract microplastics from anhydrous beach sediment.
The scope of the microplastic extraction method in this case is limited to strictly the anhydrous beach sediment. A nozzle was designed to operate at the specific terminal velocity of sediment such We address the development of a dynamic-soaring capable unmanned aerial vehicle UAV optimized for long-duration flight with no on-board power consumption. In addition to this, a 6 degree-of-freedom flight simulation environment is designed to include the effects of atmospheric wind conditions.
A simple flight control system aids in the development of the dynamic soaring maneuver. A modular design paradigm is adopted for the aircraft dynamics model, which makes it conducive to use the same environment to simulate other aircraft models.
Multiple wind-shear models are synthesized Shortly after the roll-up evolution of the vortex sheet behind the wings of an aircraft, a coherent counter-rotating vortex pair emerges. Presence of this vortex pair in the downstream of an aircraft, creates unsafe conditions for other aircraft, especially near airport runways.
Fundamental knowledge of the physics that govern the formation, duration and dissipation of aircraft wake vortices is desirable in order to improve aircraft operational safety. This study uses non-equilibrium pressure theory to develop an accurate model describing the physical behavior of the vortex pair created by an aircraft in the early to mid-field vortex regime. An isolated aircraft This bibliometric analysis in this paper aims to study the quantitative progress done in the artificial compressibility AC method-based CFD simulation and analyze its potential in solving incompressible flow simulations in computational fluid dynamics smoothly.
The sector of CFD is enhancing more and more maturely due to advancements in computing architecture, numerical methods, and simulation tools. There have been various attempts to solve the pressure-velocity coupling issue in the Navier-Stokes equation. The artificial compressibility method ACM , as opposed to pressure-correction methods, solves the incompressible equation in a non-segregated manner. With the introduction of the ACM, the system of the equation Many existing boundary layer models treat transition as a rapid switch from laminar to turbulent flow, with correlations defining properties in each respective region.
Natural transition, however, is not always a very spanwise uniform process, with the onset of transition varying somewhat between different streamwise paths of fluid flow.
Thus, a spanwise average of natural transition can result in a more gradual, extended transition region than many existing models predict. Modern applications, such as aircraft wings and fuselages, are extremely streamlined and smooth, allowing for natural transition to occur rather than flow tripping to turbulent near the leading edge.
This research determines the relation between the High-Pressure Compressor HPC blade characteristics, compressor pressure ratio, and lift-to-drag ratio of a high bypass turbofan engine. Parametric cycle analysis and computational fluid dynamics are performed to compare and validate findings. The goal of this study is to optimize the design of HPC to The main objectives of this report were to perform analysis of an ideal scramjet engine, to assess the influence of fuel on endurance factor, and the possibility of lowering the starting Mach Number of the scramjet.
In the first part, an ideal cycle parametric analysis was conducted on three different fuels i. The detailed analysis is done largely relying on a 9 step Parametric Cycle Analysis technique to study how fuel properties influence the variation of The accuracy of modern state-of-practice computational fluid dynamics approaches in predicting the cooling effectiveness of a perforated plate film-cooling arrangement is evaluated in ANSYS Fluent.
A multiphysics approach to model heat conduction through the solid geometry is shown to offer significant improvements in wall temperature and film effectiveness prediction accuracy over the standard adiabatic wall approach.
Additionally, localized gradient-based grid adaption is analyzed using The three-dimensional, unsteady, and turbulent airwake produced by a scaled model of a generic Navy ship Simple Frigate Shape No.
Stereoscopic, time-resolved particle image velocimetry TR-PIV measurements were made at six different crosswise planes over the flight deck region of the ship model, with and without the effect of a simulated atmospheric boundary layer ABL.
Spatiotemporal analyses of the TR-PIV measurements were performed using modal decomposition, and the modes were decomposed further based on the frequency contents of their time dynamics. This approach allowed an inspection of the individual scales of the Researchers have access to the McGill High Performance Computing HPC centre, which operates one of the most advanced computing and data management facilities in Canada and the world. McGill HPC is equipped with processing cores with both graphical processing units and Intel Phi accelerators and provides extensive data storage, cloud-computing services, and advanced technical support and HPC consulting to McGill researchers.
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