Aerodynamic Performance Of USM EFA-1 Remotely Piloted Vehicle [UG1242.D7 Z96 2004 f rb] [Microfiche 7609].

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

Aerodynamics prediction of multi-purpose UAV using wind tunnel experimental approach / Ghazirah Mustapha @ Mustafa, Zurriati Mohd Ali, Wirachman Wisnoe

Aerodynamics is a branch of dynamics concerned with the study of fluid flow and the interaction of the atmosphere around the objects. The calculation of important performance indicator such as forces and moments acting on an object can be made with the deep understanding of the motion of air around an object. In aviation, aerodynamic is one of the most important fields to consider when designing a new or modifying the existing airplane. The collections of aerodynamic database, for example lift, drag and moments force will help the designers and aeronautical engineers to improve the aerodynamic design and the performance of the airplane. Since the first airplane has been developed, the design and performance of the airplane is getting better. Many years of studies in aerodynamics leads people to find a way and solutions on how to makes airplane or any flying object to get the maximum capability in speed, performance, ability in any maneuvering and prediction of forces and moment. Aerodynamics investigation and analysis can be classified according to the ratio of the problem’s characteristics flow speed to the speed of sound. Subsonic is a second classification of aerodynamics which all the speed in the problem are less than the speed of sound. At present, the design of unmanned aircraft vehicle,UAV is one of the most challenging tasks in aerodynamic studies. In UAV design, the placement of the wing, tail and canard is somehow, not the same as in the conventional airplane configuration. There are a lot of UAV designs such as peanut shape (Canadair CL-227 Sentinel), VTOL UAV with counter-rotating blades and variation of shapes in the planform wings and tails. These configurations need a lot of aerodynamic skills and knowledge to ensure that the UAVs can safely take off, loiter and land

Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

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 with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft

Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

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 with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft

Study on the potentiality of power generation from exhaust air energy recovery wind turbine: a review

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 Air Energy Recovery Wind Turbine. The potentiality of wind extractions is reviewed to achieve the clear overview of this new progressive ideas and the important configurations is accentuated. Most findings indicated that this energy recovery device converts wasted energy to a more profitable form by converting it to electricity, resulting in a rapid return on investment. Moreover, the enclosing the output area of wind turbines for recovering energy enhances overall efficiency

Aerodynamic performances of paper planes

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 aerodynamic efficiency () performances for each paper planes. The results show that the Glider paper plane has managed to produce better performances in terms overall magnitude, stall angle, wider angle of attack (?) envelope and higher maximum lift coefficient magnitude compared to the other paper plane design. However, Glider paper plane has the least distributions by producing at least 14.3% larger magnitude compared to the other plane design at certain ? region. Instead, The Wide Stunt has promisingly produced better distribution by producing lower value compared to the other plane design. Based on performance, the Wide Stunt paper plane has produced better and maximum aerodynamic efficiency () magnitudes compared to the other design. Wide Stunt paper plane induced at least 6.4% better magnitude compared to the other paper plane design. Based on these results, it can be concluded that Wide Stunt paper plane has promising advantages which are very crucial for the paper plane especially during hovering operation, take-off and landing manoeuvre

Wind tunnel experiment of UTM-LST generic light aircraft model with external store

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 × 106 and 0.6 × 106 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