Conceptual design of Blended Wing Body for Future Air Transportation

Blended wing body is a fixed wing aircraft which are smoothly blended together with no clear dividing line and no distinct wings also be given a wide Aerofoil shaped body. The future transportation is of aircrafts will incline towards the aerodynamically efficient and capable of carrying large number of passengers over long range and environmental benefits is the main paradigm in the design of aircraft BWB has a high lift to drag ratio which increases the CL max and velocity of the airplane with high load factor and high economy compared with traditional aircraft. Evacuation pressure or the cabin pressurization is the major issues in most of the designs with the minimum aerodynamic lift coefficient and drag coefficient. On the other side of the trend is towards the increasing cruise speed. High speed flow is connected with overcoming of intensive drag rise accruing due to existence of intensive shock, closing local area of supersonic flow. Increase of flight Mach number is possible only by using flow control methods and through affecting the shock increases of aspect ratio leads to increase of lift coefficient corresponding to maximal lift to drag. High bypass ratio engines have smaller fuel consumption and lower noise level but have negative effect on flow around airframe including take-off and landing phases. The necessity of solving problem of intensive aerodynamic heating of surface element of flight vehicles and by ensuring of their stability and controllability and also by need of implementing of high-volume tanks for hydrogen fuel and super high bypass ratio engines.

IMPLEMENTATION OF TRANSONIC AREA RULE AND SWEPT BACK DELTA WING DESIGN ON AN AIRCRAFT.

The transonic area rule was first implemented in the 1950s. It is an important concept related to the drag on an aircraft or other body in transonic and supersonic flight which states that two airplanes with the same longitudinal cross-sectional area distribution have the same wave drag, independent of how the area is distributed laterally. A swept back delta wing increases the critical Mach number of the wing and performs well at low speeds, as a result of unique swirling vortices that form on the upper surface of the wing. BOOM Supersonic plans to bring back Supersonic Commercial aircrafts by implementing these modifications in the famous Concorde. In this paper two aircraft designs inspired by Concorde and BOOM Overture are compared using ANSYS Fluent. These were designed in CATIA with changes in fuselage dimensions, wing configuration and engine configuration. The lift to drag ratio of both the designs are calculated and compared. Pressure contours, velocity vectors, vector pathlines, turbulence pathlines and pressure pathlines are also compared. The results show that the design with the implementation of transonic area rule and swept back delta wing has a better Lift to Drag ratio when compared to the design with a wide fuselage and a delta wing design.

Effect of Ground Proximity on Aerodynamic Characteristics of NACA 4412 Airfoil.

Ground effect plays a vital role in modulating the flow behavior over any streamlined body. The most widely used wing-in ground effect (WIG) aircrafts and seaplanes utilize this phenomenon in order to enhance the aerodynamic performance during the landing and take-off phases of flight. This paper investigates the aerodynamics of ground effect on a NACA 4412 rectangular wing without end plates. The experiment was conducted in a low-speed wind tunnel at Re=2×105 for the ground clearance of 1 and 0.5 of the chord, measured from the maximum thickness position on the airfoil. The pressure distribution over the chord length was recorded for α=3° and 6° to verify the effect of ground clearance during takeoffs. The results have shown to be in good accordance with the literature, as the coefficient of lift augmented with increase in ground proximity and the induced drag was minimized.

Computational Fluid Dynamic Analysis of Vortex Generators on MAV.

Micro Vortex generators are very small components deployed on the wings to control airflow over the upper surface of the wing to affect the boundary layer over it. These are employed onto a Micro aerial vehicle (MAV) of fixed wing type with an S5010 which is a low Reynolds number airfoil. This airfoil provides good aerodynamic results as compared to many low Reynolds number airfoils. Micro vortex generators are used to enhance the performance through controlling airflow at different speeds and angle of attack. The comparison of a half part of the MAV wing which is designed in CATIA, with and without the vortex generators on its leading edge at 10% of its chord length is done to show how the vortex generators improve the performance and control authority at different speeds and angle of attacks. These are shown with the velocity and pressure distribution around the wing by considering laminar flow in the simulation.

Synthesis of Aerogel with Graphene and Significance with Aerospace Industry

The Primarily focus on Graphene Aerogel, its synthesis and structural integrity together with high electrical conduction. Graphene could be a new nanocarbon that has, single-, bi- or few- layers of carbon atoms forming membered rings. Mechanically powerful and electrically semiconductive graphene aerogels will be produced by either essential drying or freeze of gel precursors integration from the reduction of graphene substance with L-ascorbic acid. In distinction to ways in which utilize physical cross-links between GO, this approach provides valency carbon bonding between the graphene sheets. The graphene aerogels put together possess large surface areas and pore volumes, creating those materials to a feasible possibility to be used in energy repository, catalysis, and sensing applications. We've additionally showcased some applications for Graphene Aerogel such as their electrical conductivities, Lithium-ion batteries and electrical phenomenon devices, Supercapacitors and photocatalysis.

Aerodynamic Analysis of an Arrow with Different Fletch Configurations: A Computational Approach

Archery is being contemplated from hundreds of years; however there have been not many investigations expressing and clarifying the optimal design and aerodynamic effectiveness of an Arrow. Presently Archery has turned into a significant game in Olympics. Every nation is showing colossal interest in delivering champions. So, it is important to work on the solidness of the Arrow to such an extent that its precision and aerodynamic characteristics improve. Broad examination is proceeding to work on the streamlined exhibition of the Arrow. So, this study intends to explore the aerodynamic characteristics of an Arrow for various fletches and diverse Arrow points. To accomplish this, the initial trends of aerodynamics characterization were obtained by XFLR5 v6.51 and then deep flow analysis was performed by Computational Fluid Dynamics using ANSYS Fluent. The outcomes are upon to show that the Arrow performs better at a speed range of 40-60 m/s and angles of attack from - 5 to +5 degrees. MATLAB is employed in plotting all of the non-dimensional data fluctuations, since it is the most trusted plotting software. The outcomes are validated with existing research work and significant conclusions are obtained.

Finite Element Study on the Effect of Geometrical Parameters on the Mechanical Behavior of 3D Reentrant Auxetic Honeycombs.

Auxetic materials are a special case of cellular materials, which exhibit a negative Poisson’s ratio. This in fact is the reason behind their peculiar behavior i.e. lateral shrinkage under longitudinal compression and vice versa. Since these materials do not obey the laws of “normal” materials and go beyond common sense, they are still an emerging class which can be put to use for various purposes like self-locking reinforcing fibers in composites, controlled release media, self-healing films, piezoelectric sensors, and also be used in biomedical engineering. Their stress-strain behavior, Poisson’s ratio and impact energy absorption are controlled by bulk material as well as the unit cell geometry. Among many forms of auxetic structures available, we have chosen a three-dimensional reentrant auxetic honeycomb unit cell. The unit cell geometrical parameters were taken from literature. In this study, we try to understand the effects of strut angle through finite element simulations while keeping the bulk material, unit cell size, strut thickness and number of repetitions constant. A total of three different angles were tested, based on which we conclude that as angle increases, the Poisson’s ratio increases and Energy absorption is maximum at 30 deg.

Aerodynamic characteristics of owl like airfoil at low reynolds number.

The computational investigation of aerodynamic characteristics and flow fields of a smooth owl-like airfoil without serrations and velvet structures.The bioinspired airfoil design is planned to serve as the main-wing for low-reynolds number aircrafts such as (MAV)micro air vechiles.The dependency of reynolds number on aerodynamics could be obtained at low reynolds numbers.The result of this experiment shows the owl-like airfoil is having high lift performance at very low speeds and in various wind conditions.One of the unique feature of owl airfoil is a separation bubble on the pressure side at low angle of attack.The separation bubble changes location from the pressure side to suction side as the AOA (angle of attack) increases. The reynolds number dependancy on the lift curve is insignificant,although there’s difference in drag curve at high angle of attacks.Eventually, we get the geometric features of the owl like airfoil to increase aerodynamic performance at low reynolds numbers.

DESIGN OF A CANARD-WING UAV

In this project, we intend to design a Canard wing-based Unmanned Aerial Vehicle (UAV), which can carry a wide range of missions, providing capabilities to handle our challenges with sophisticated care. Canard-based UAV is the latest trend in aviation technology designed for the use case of providing better maneuverability, which in result gives the UAV new capabilities, such as increased time for data gathering, transferring, and autonomous behavior. The basic disciplines like Aerodynamics, Engineering design, Flight dynamics, Propulsion, and Performance are carried out during the UAV designing process. The proposed methodology applied in this project is weight estimation, initial sizing, aerofoil and wing geometry, fuselage sizing, tail sizing, T/W ratio, aerodynamics, and performance analysis. The design of Canard Based UAV leads to a deeper understanding of the trade-off studies of the UAV and is demonstrated by optimizing for designed missions like surveillance. A drafted sketch is presented at the end of the design phase featuring the selected configurations of major components.

Fabrication and Mechanical Properties of PAN-based Carbon Composite Laminates for High Temperature Applications.

The main aim of this paper is an experimental investigation is to study the thermophysical and mechanical properties of polyacrylonitrile (PAN) based carbon fiber fabric and phenolic resin composites (Cf-PR) for thermal protection system (TPS) for high temperature applications. Composite laminates of Cf-PR were prepared by hand-layup method by considering the curing temperature of 1500 C at 100 kg/cm2 for 4hrs under hydraulic hot press machine. The mechanical properties of the materials such as the interlaminar shear stress (ILSS), flexural strength, compression strength, bar coal hardness, thermal property such as thermal conductivity and physical property such as density were studied. It was shown that the thermophysical and mechanical properties are responsibility for the higher strength and higher temperature applications for TPS.