Papers by El Mehdi Laamarti
This study focuses into the analysis of subsonic viscous aerodynamic flow over an airfoil, employ... more This study focuses into the analysis of subsonic viscous aerodynamic flow over an airfoil, employing Matlab for numerical simulations and utilizing existing experimental data for validation. By examining key parameters like angles of attack, Reynolds numbers, and surface conditions, the study aims to advance our comprehension of airfoil performance. The outcomes provide valuable insights for optimizing airfoil designs in diverse applications such as aircraft and wind turbines, fostering the development of more efficient and sustainable aerodynamic solutions. The investigation specifically focuses on evaluating the coefficient of pressure, wall shear stress, and skin friction for a NACA 0012 airfoil at a freestream Reynolds number of 2 million.
The current project is a study of the transonic regime flows over an airfoil for which shock wave... more The current project is a study of the transonic regime flows over an airfoil for which shock waves have a major impact on the global performance in transport aircraft. The non-linearity of the unsteady euler equation is difficult to solve using the classical schemes and the convergence is very slow. In fact, these classical calculation methods are now ubiquitous in the science of aerodynamics. The J.D. Cole and E.M. Murman scheme is an alternative to solve the non-linearity of the problem through the transonic small disturbance equation. In what follows, this mixed elliptic-hyperbolic differential equation is solved using finite difference methods and shock wave appears through iterative algorithms where relaxation parameter is introduced to converge faster.
The current project is a study on the aerodynamics of the VKI turbine blade cascade corresponding... more The current project is a study on the aerodynamics of the VKI turbine blade cascade corresponding to the 1 rst stage gas turbine that is cylindrical in design. The 3D computational Fluid dynamics software CFX will be used to simulate the flow through the VKI blade cascade for defined operated conditions. The simulation will run by solving the Navier Stokes equation and using the k-turbulence model at a high resolution. A detailed explanation of the methodology and the choices made to simulate the cascade will be presented. Then an investigation and a discussion will be made on different flow parameters as the pressure, velocity, temperature contour, Mach number distribution and losses to explain the performances found. The findings show the formation of a separation flow in the aft part of the blade suction surface.
2D Laplace Equation
The current project is a study of the Laplace equation that is used nowadays in many applications... more The current project is a study of the Laplace equation that is used nowadays in many applications related to the electrical, magnetic, gravitational potentials, steady state temperatures, and in hydrodynamics.. The system corresponds to an elliptic second order partial differential equation and is widely used in the study of the inviscid incompressible potential flow in fluid mechanics. To solve this equation, numerical methods are used and different schemes are introduced to better control the solution through stability, accuracy and consistency. In what follows, a numerical study and investigation of the 2D Laplace Equation.
Gas Dynamics
The project is about studying the whole rocket. We will work on comparing between analytical and ... more The project is about studying the whole rocket. We will work on comparing between analytical and theory results on the converging diverging (C-D) nozzle, also called de Laval nozzle for an isentropic flow, a normal shock wave in the diverging section, an oblique shock wave and an expansion at the exit. Then we will simulate the flow at the upper surface of the rocket by CFD, considering the upper area as diamond shaped. The aim of the simulation is to show the oblique shock wave created by supersonic speed and doesn’t intersect with the rest of the rocket, reducing overall the drag.
Gas Turbine Design, 2021
Pratt & Whitney Canada is currently seeking risk sharing partners for the design, development and... more Pratt & Whitney Canada is currently seeking risk sharing partners for the design, development and eventual production of a new family of Gas Turbine Engines. The new family of engines will be a 3 shaft Turboshaft arrangement used mainly at 4000 ft altitude where the ambient temperature is 74 degF. The engine configuration will be a single stage low pressure compressor (LPC) driven by a single stage low pressure axial turbine (LPT), followed by a centrifugal high pressure compressor (HPC), driven by a single stage high pressure axial turbine (HPT). The helicopter rotor will be driven through a reduction gearbox, by a single stage power turbine (PT). The contribution to the partnership will be the design and development of the core rotating components of the engine (HPC & HPT).
Numerical Methods for the linear-Advection Equation, 2020
The current project is a study of the 1-D linear advection equation that characterize the waves a... more The current project is a study of the 1-D linear advection equation that characterize the waves and represent the transport of substance by bulk motion.The system corresponds to an hyperbolic partial differential equation and takes a big interest when it comes to the study of the normal shock wave. To solve this equation, numerical methods are used and different schemes are introduced to better control the solution through stability, accuracy and consistency. In what follows, a numerical study and investigation of the 1-D Linear Advection Equation.
Current project is a study on the aerodynamics of an airfoil. Indeed the goal will be a study on ... more Current project is a study on the aerodynamics of an airfoil. Indeed the goal will be a study on a NACA 2424 to know it’s characteristics. For this, we will be using the source panel method to obtain the source strength distribution required to generate the airfoil. We will change the parameters to see the influence of each on the final results. Then we will use the Thin airfoil theory to obtain the lift coefficient as well as the center of pressure of the airfoil for different angle of attack.
The current project is an attempt to make a contribution to ICAO's one of the aspirational goals ... more The current project is an attempt to make a contribution to ICAO's one of the aspirational goals for sustainable aviation. The project aims to perform analysis on combustion characteristics and NO emissions for the combustion of a mixture of Ammonia and Hydrogen as carbon-free alternatives to existing aviation fuel. The work will be also compared with different mechanisms and with experimental data.
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Papers by El Mehdi Laamarti