Firdaus Mohamad

• Doctor of Philosophy
• Lecturer at MARA University of Technology

Large-Eddy Simulations (LES) for an oscillating NACA0012 aerofoil at Reynolds number 1.35 × 105 have been performed to investigate the capability of a new approach of a One-equation SGS model. The phenomena of the oscillating aerofoil at higher amplitude angle (𝛼𝑎𝑚𝑝) is believed to produce deep dynamic stall in which strong non-equilibrium turbulen...

Prediction of laminar-transition flows around an airfoil remain an issue in the large eddy simulation (LES) community. Hence, this paper aims to solve this issue by introducing a new dynamic one-equation kSGS model (OD). This model uses the advantage of the dynamic Smagorinsky procedure to represent the energy transfer between grid-scale (GS) and s...

Proton Exchange Membrane Fuel Cell (PEMFC) is a device that generates electricity through an electrochemical reaction of oxygen air and hydrogen fuel. Thetransportofoxidantand fuel through the bipolarplatesis a significant factor affecting the cell performance. Currently, present work concentrates highly on flow field layout and channels design con...

This paper describes the determination of a relative delamination size of the skin to the honeycomb core of the honeycomb sandwich panel using the Finite Element Method approach. In the analysis, the honeycomb sandwich panel was modelled in the actual dimension using CATIA. The delamination of two different sizes (10 mm diameter and 30 mm diameter)...

In this paper, a study of aerodynamic characteristics of UiTM's Blended-Wing-Body Unmanned Aerial Vehicle (BWB-UAV) Baseline-II in terms of side force, drag force and yawing moment coefficients are presented through Computational Fluid Dynamics (CFD) simulation. A vertical rudder is added to the aircraft at the rear centre part of the fuselage as y...

This paper presents a study about yaw stability analysis for UiTMs Blended-Wing-Body (BWB) Baseline-II E-4. This aircraft is equipped with split drag flaps in order to perform directional motion. One of the split drag flaps will be deflected to generate yawing moment. This yawing moment is generated through the drag that is produced upon deflection...

Fuel cell water management has two conflicting requirements; too less water causing membrane dehydration and too much water causing liquid water flooding. Both phenomena resulting in significantly instability voltage performance because of imbalance water presence. Therefore, it is vital to analyze and understand the root cause of the problem hence...

A formula-type car design with fendered rear tyres is chosen as the ARTeC's design for 2011 Perodua Eco-Challenge. This paper aims at investigating aerodynamics of ARTeC's EMo-C car, measuring drag coefficient in particular and observing airflow around the body. There are two means of measuring the drag, the first is by simulating the air flow via...

This paper discusses on the split drag flaps to the yawing motion of BWB aircraft. This study used split drag flaps instead of vertical tail and rudder with the intention to generate yawing moment. These features are installed near the tips of the wing. Yawing moment is generated by the combination of side and drag forces which are produced upon th...

This paper presents a study about split drag flaps as control surfaces to generate yawing motion of a blended wing body aircraft. These flaps are attached on UiTM’s Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) Baseline-II E-4. Deflection of split drag flaps on one side of the wing will produce asymmetric drag force and, as consequences, ya...

the BWB. The aerodynamic characteristics prediction of BWB­ Baseline II E2 aircraft was obtained through CFO analysis using unstructured mesh and standard one - equation turbulence model, Spalart-Allmaras was selected in the investigations. Lift coefficient (CL), drag coefficient (CD) and moment coefficient (CM) were studied at flight condition of...

A study of the effect of canard to Baseline-II blended wing-body aircraft is presented here with emphasis on investigating contributions of canard's various setting angle to aerodynamic parameters and longitudinal static stability. A computational fluid dynamic (CFD) simulation has been conducted at low subsonic speed to collect aerodynamic data an...

This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle....

This paper describes the wind tunnel testing of a Blended Wing Body (BWB)-Baseline I with elevator developed in Universiti Teknologi MARA (UiTM). The experiment work was carried out in UiTM low speed wind tunnel using 1∶7 scaled model of BWB at Mach 0.1. The testing is conducted for center elevator angle between −10° to +10° until stall angle. The...

An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing-body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canar...

This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline-I and the new model known as BWB Baseline-II. The Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to its predecessor while maintaining wingspan. T...