Papers by DR. ZURRIATI MOHD ALI
JOURNAL OF APPLIED ENGINEERING DESIGN AND SIMULATION
Glider is a fixed-wing aircraft which does not depend on the engine. A glider can fly for an exte... more Glider is a fixed-wing aircraft which does not depend on the engine. A glider can fly for an extended period depending on the design and area of the lifting surface. Just like any other aircrafts, the design of wings is crucial to produce lift force to keep aircraft in the air. Gliders have long wings and is designed to be lightweight which allows it to have a high lift-to-drag ratio (L/D) to glide at a long distance. The maximum lift-to-drag ratio, 〖(L/D〗_max) can indicate how far the glider will glide as it is one of the most important performance parameters. This project aims to design, build, and fly an energy glider. Prior on the design of the energy glider, statistical analysis has been done by comparing data from many studies to aid in determining the initial values of the glider. Then, the general design of the energy glider has been decided during the preliminary design. To support the design decision made, ANSYS Fluent software has been used to study flow of air over KFm-5...
Evergreen, 2021
This work aims to characterize the lift (CL) and drag (CD) coefficient distributions on the curre... more This work aims to characterize the lift (CL) and drag (CD) coefficient distributions on the current Neo-Ptero micro-UAV prototype. A CL analysis on Neo-Ptero shows that the model has a promising CL performance throughout the α increment. For every 2° angle of attack increment, the model can generate approximately 22% increment in CL magnitude. Neo-Ptero also has a decent magnitude in maximum lift coefficient and stall angle at 1.24 and 18°, respectively. CL comparison works reveal that Neo-Ptero performs better than the other micro-UAV model produce by Ming from National University of Singapore (NUS) and also Serindit (produced by UAV team from University Riau, Indonesia) particularly in terms of α range and CLmax magnitudes. However, Neo-Ptero suffers from severe CD generation by producing an average of 23.8% rise in CD magnitude for every 2° angle of attack increment. A CD comparison study in performance reveals that compared with other micro-UAV models, Neo-Ptero induces at least 13.2% and 5% larger CD magnitude and CD increment, respectively
Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 2021
This paper presents the investigation and improvement of lift and drag characteristics of Neo-Pte... more This paper presents the investigation and improvement of lift and drag characteristics of Neo-Ptero micro-UAV models based on the virtual wind tunnel method. Despite its successful development and flight stability, the lift and drag coefficients characteristics of the current Mark 1 Neo-Ptero remain unknown. To improve the Mark 1 Neo-Ptero performances, Mark 2 Neo-Ptero model has given a new unsymmetrical airfoil wing configuration. The computational aerodynamic analysis was executed and focused on certain lift and drag coefficient characteristics. Lift coefficient results showed that Mark 2 improved in overall lift characteristics such as zero-lift angle, maximum lift magnitude and stall angle magnitude. Conversely, Mark 2 model suffered a slightly higher drag coefficient magnitude and more significant drag increment percentage than Mark 1. However, the trade-off between superior lift magnitude and minor drag generation induced by Mark 2 boosts the model’s aerodynamic efficiency pe...
The effect of canards configurations to the aerodynamics of the blended wing body / Wahyu Kuntjoro, Wirachman Wisnoe and Zurriati Mohd Ali
The Blended Wing Body known as “Baseline-I” was started in 2005 in Universiti Teknologi MARA. The... more The Blended Wing Body known as “Baseline-I” was started in 2005 in Universiti Teknologi MARA. The aircraft has 2 meter length and 4 meter wingspan. Since then, several studies had been carried out by a group of UiTM lecturers on BWB using Computational Fluid Dynamics (CFD) and wind tunnel experiments. They found out that the BWB can fly at very high angle of attack. The maximum lift is achieved at the angle of attack around 34 - 39. However, the wing has stalled at angle of attack around 8, which is considered too low. A study on the effect of center elevator deflection to the aerodynamics of BWB “Baseline-I” was also carried out, using CFD simulations. The result shows that elevator deflection has no significant effect in terms of lift, drag and lift to drag curves. Currently, Universiti Teknologi MARA is designing a BWB with canard known as “Baseline-II”. It has a simpler planform, broader-chord high-swept wing and slimmer body with a canard (front wing) as a longitudinal contr...
The Blended Wing-Body (BWB) aircraft is an unconventional aircraft that offers the aerodynamics p... more The Blended Wing-Body (BWB) aircraft is an unconventional aircraft that offers the aerodynamics performance advantages compared to the conventional aircraft. This type of aircraft has a unique design where the main body is blended together with the wing that gives the additional lift of the aircraft. In contrast to the conventional aircraft, the BWB has a poor stability due to the absence of the tail. A possible solution is by using a horizontal control surface, the canard, to improve the stability of the BWB. For this purpose, a comprehensive investigation of the aerodynamic behavior of the BWB with canard is important. The Computational Fluid Dynamics (CFD) and experimental testing were conducted to obtain the aerodynamics parameters of the BWB; lift, drag and moment coefficient. The BWB with different canard aspect ratio (AR) were compared with the BWB without canard to study the effect of the canard to the BWB and to assess which aspect ratio of the canard is beneficial to the B...
Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 2021
Presently the worldwide lockdown from Covid-19 give a huge effect on different sectors across the... more Presently the worldwide lockdown from Covid-19 give a huge effect on different sectors across the board, notably on energy consumption. Lockdowns have fuelled the intensification of low-carbon resources in terms of electricity production, yet a drastic upswing in electricity use in residential districts during the pandemic. By exploring economic renewable energy resources, the world is trying to overcome the crisis and one of them is wind energy, where this sustainable energy system is highly demanded, thus reducing global CO2 emissions. Researchers have carried out several findings on wind energy obtained from wind turbines at various potential locations, but most of it used natural sources as a wind stream. Therefore, a revolutionary concept on extracting clean energy from manufactured wind resources with wind turbine system for power generation is introduced in recent studies. The main goal of this review paper is to emphasize the performances of power generation through Exhaust ...
IOP Conference Series: Materials Science and Engineering, 2020
Blended Wing Body Aircraft (BWB) is an unconventional aircraft that combined the conventional and... more Blended Wing Body Aircraft (BWB) is an unconventional aircraft that combined the conventional and flying wing aircraft’s design. The unique design of the BWB offers a high fuel efficiency, low noise, and large payload volume for the size of aircraft. However, the BWB is unstable due to the absence of the its vertical stabilizer. A possible solution to improve this problem is using a horizontal control surface, the canard. For this purpose, the numerical simulation using NUMECA Computational Fluid Dynamic (CFD) software were conducted to obtain the aerodynamics forces subjected on this aircraft. The lift coefficient (CL), drag coefficient (CD) and moment coefficient (CM) are analysed at Mach number 0.1. The study is specifically to discuss the effect of canard setting angle ™ of BWB from ™ = -10° to 10° in that particular of aspect ratio (AR 2, 4, 6 and 8) towards aerodynamics parameters, CL, CD, and CM.
International Review of Mechanical Engineering (IREME), 2018
This paper discusses the impact of the external store on the aerodynamic performance of the light... more This paper discusses the impact of the external store on the aerodynamic performance of the light aircraft model in the subsonic region. Light aircrafts are commonly used for pilots training, survey, leisure and transportation. To date, there have been a lot of small aircrafts used for strategic purposes where an external store, either external fuel storage or armament, has been installed on its wing. Examples of such aircraft are KAI-KA1, A29 Super Tucano, and Beechcraft AT-6. Therefore, it is important to study the effect of this external store installation on the aerodynamic characteristics of a small aircraft. An available light aircraft model of UTM Low speed wind tunnel (UTM-LST) has been modified so that a generic external store can be mounted on the lower surface of the wing. Two set of experiments were carried out on the model which were; experimental with an external store followed by experimental without external store as a benchmark of tested configuration. The experiments were conducted at two different speeds of 26 and 39 m / s that correspond to Reynolds numbers 0.4 × 10 6 and 0.6 × 10 6 respectively. Three measurement techniques were employed on each configuration. The first measurement was the 6 component forces and moments measurement technique. The second technique was the pressure measurement on the wing, and the final test was the tufts flow visualization. The result of steady balance indicated that the external store has no effect on the coefficient of lift at low attack angle. However, it showed that there was a reduction of lift coefficient by 2% at higher angle of attack. The data showed that the coefficient of drag increases by 4% when the external is installed. Surprisingly, the installation of the store has insignificant effects on the pitching moment coefficient. An interesting feature observed from surface pressure studies where, the results showed that the pressure coefficient increased when the external is mounted on the wing at a low angle of attack. Such changes, however, do not occur at high angle of attack.
A blended wing body airplane with a close-coupled, tilting tail
IOP Conference Series: Materials Science and Engineering, 2016
This paper highlights a novel approach to stabilizing and controlling pitch and yaw motion via a ... more This paper highlights a novel approach to stabilizing and controlling pitch and yaw motion via a set of horizontal tail that can act as elevator and rudder. The tail is incorporated into a new design of blended wing body (BWB) aircraft, known as Baseline-V, located just aft of the trailing edge of its inboard wing. The proposed close-coupled tail is equipped with elevators that deflect in unison, and can tilt - an unusual means of tilting where if starboard side is tilted downward at k degree, and then the portside must be tilted upward at k degree too. A wind tunnel experiment is conducted to investigate aerodynamics and static stability of Baseline-V BWB aircraft. The model is being tested at actual flight speed of 15 m/s (54 km/h) with varying angle of attack for five elevator angle cases at zero tilt angle and varying sideslip angle for four tilt angle cases at one fixed elevator angle. The result shows that the aircraft's highest lift-to-drag ratio is 32. It is also found that Baseline-V is statically stable in pitch and yaw but has no clear indication in terms of roll stability.
Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low pitching angle
2010 International Conference on Science and Social Research (CSSR 2010), 2010
AbstractThis paper discusses the influence of canard deflection angle on the aerodynamics charac... more AbstractThis 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 experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed
2010 International Conference on Science and Social Research (CSSR 2010), 2010
Abstract An experimental investigation is conducted to obtain aerodynamic characteristics and pe... more Abstract 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 ...
Journal of Wind Engineering and Industrial Aerodynamics, 2009
Aerodynamic characteristics of a square prism in a uniform flow for various angles of attack have... more Aerodynamic characteristics of a square prism in a uniform flow for various angles of attack have been investigated using LES turbulence model. The results show that mean aerodynamic coefficients, surface pressures, and flow patterns for all angles of attack agree favorably with experiments. In addition, spanwise length of computational domain is found to slightly influence the mean aerodynamic coefficients whereas it shows strong impacts on fluctuating aerodynamic coefficients, which motivates a development of grid-independent estimation method for quantitative evaluations of fluctuations. The predicted power spectral densities for fluctuating aerodynamic coefficients are in good agreements with experiments in primary frequencies, which can be explained by the flow patterns. Strouhal numbers obtained from the simulations also agree well with experiments and acute change observed around 141 is successfully captured. Finally, a method for estimating grid-independent fluctuating aerodynamic coefficients is proposed by using a systematic elongation of spanwise length and is validated by the numerical tests.
Preliminary Design of Baseline-II Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV): Achieving Higher Aerodynamic Efficiency Through …
… of EnCon2010, 3rd …, 2010
Pesawat tanpa juruterbang merupakan satu bidang yang agak baru di negara kita Malaysia. Remotely ... more Pesawat tanpa juruterbang merupakan satu bidang yang agak baru di negara kita Malaysia. Remotely Piloted Vehicle (RPV) in our country Malaysia, still in an early stage
Computational Aerodynamic Analysis of UiTM's Hawkeye UAV Aircraft
This paper discusses the aerodynamic characteristics of Hawkeye UAV aircraft with a forward-swept... more This paper discusses the aerodynamic characteristics of Hawkeye UAV aircraft with a forward-swept wing configuration. The unconventional wing design on Hawkeye allows for better maneuverability and stability during a field test but there were no prior studies on its aerodynamic characteristics. A series of CFD simulations were conducted using ANSYS Fluent to obtain the aerodynamic characteristic of Hawkeye; lift, drag and moment coefficient. A full-size model and Reynolds-averaged Navier-Stokes (RANS) numerical method-based equations, Spalart-Allmaras turbulence model was used for the simulation. The angle of attack of the aircraft differs from -10° to 30° with an interval of 2° at a flight condition of Mach number 0.1 (~35 m/s). The CFD results obtained will be used to calculate the aircraft performance in a real field test and for future improvement of the UAV.
Aerodynamic Performances of Paper Planes
Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
Paper plane has a high potential to be upgraded as a Micro Air Vehicle (MAV). Due to its simplici... more Paper plane has a high potential to be upgraded as a Micro Air Vehicle (MAV). Due to its simplicity, paper plane offers easier design option compared to the biological inspired designs as shown in recent MAV development. However, researchers have underestimate and overlook the basic aerodynamic performance induced by these paper planes. This is due to its common usage as toys and wide range of paper plane design. Thus, the objective for current work is to analyse and compare the aerodynamics forces and its performance for selected paper plane design known as Glider, Wide Stunt Glider Plane and Stunt plane. A series of CFD simulations on each paper plane was executed by using ANSYS-CFX module. A steady state, incompressible flow Navier-Stokes equation (RANS) combined with Shear Stress Turbulence (SST) model were used in this works to solve flow problem over the paper planes. The analysis is mainly conducted to study and compare the lift coefficient (), drag coefficient ()and aerodyna...
MATEC Web of Conferences
This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended... more This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration...
The Blended Wing-Body (BWB) aircraft is an unconventional aircraft that offers the aerodynamics p... more The Blended Wing-Body (BWB) aircraft is an unconventional aircraft that offers the aerodynamics performance advantages compared to the conventional aircraft. This type of aircraft has a unique design where the main body is blended together with the wing that gives the additional lift of the aircraft. In contrast to the conventional aircraft, the BWB has a poor stability due to the absence of the tail. A possible solution is by using a horizontal control surface, the canard, to improve the stability of the BWB. For this purpose, a comprehensive investigation of the aerodynamic behavior of the BWB with canard is important. The experimental works were performed on a scale model and tested in a low speed wind tunnel. Angles of attack, varied from-10 to 10 degree, as well as canard setting angles, . The investigations were carried out at Reynolds Number of 3 x 105. The results show that the canard contributes a small lift forces but with the increase of drag to the BWB. On the stability issue, the canard with higher aspect ratio has a significant effect towards the moment coefficient of the aircraft configuration where it improves the trim angle and moment at zero lift. All these results are encouraging enough for the canard to be considered as mechanism for controlling the longitudinal mode of the BWB aircraft.
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Papers by DR. ZURRIATI MOHD ALI