Vishnu Kumar Gettin Chitharanjan

This research paper investigates the feasibility of manufacturing a Mini Turbojet Engine with a centrifugal compressor using a combination of stainless-steel pa This research paper investigates the feasibility of manufacturing a Mini Turbojet Engine with a centrifugal compressor using a combination of stainless-steel pa

The present study proposes to design, fabricate and test the solid rocket thruster using the KNSU propellant consisting of Potassium Nitrate as the Oxidizer and The present study proposes to design, fabricate and test the solid rocket thruster using the KNSU propellant consisting of Potassium Nitrate as the Oxidizer and

This research aims to explore the effect of the co-flow jet (CFJ) airfoil injection jet velocity, injection height, and injection mass flow rate on the aerodynamic coefficient through numerical analysis. Five distinct circumstances are generated by adjusting the jet velocity, injection height, and mass flow rate, and each of the cases underwent numerical investigation. For this computational analysis, Reynolds averaged Navier–Stokes (RANS) solver has been utilized by employing the Spalart–Allmaras turbulence model, and the flow is treated as incompressible. The higher injection slots reduce the coefficient of lift (CL) due to poor aerodynamic shape, which can be overcome by injecting higher jet velocities, whereas lower jet velocities injecting into lower injection slots do not raise the CL even though they have streamlined aerodynamic shape. Hence, even if CFJ airfoils with poor geometry perform less aerodynamically, this problem is not intractable because it can be solved by injecting high jet velocities; meanwhile, injecting low velocities will result in reduced aerodynamic performance for CFJ airfoils with good geometry. The CFJ airfoil with the highest jet velocity and lowest injection slot increases the CL by a maximum of 65% compared to the baseline airfoil, which is higher than all other CFJ airfoils taken into consideration.

The induced drag created by wingtip vortices has a significant impact on aircraft performance. Winglets are wingtip extensions that are intended to reduce the creation of vortices and increase the fuel efficiency. The present study is based on analyzing different winglets planform for aircraft at various angles of attack (AOA) to improve the aerodynamic efficiency. The Finite Volume Method in pressure-based solver along with the Realizable k - ɛ turbulence model, with standard atmospheric boundary conditions is used to do the CFD computations in ANSYS Fluent. According to the findings, an optimized BLERAK (Blended + Raked) winglet from the present study has a substantial impact on aerodynamic efficiency when compared to conventional winglets, and it is projected to yield a higher lift-to-drag ratio. The blerak winglets model gives 1.5 to 2% drag reduction than the other winglet models at angle of attack variations of 8°, 12° and 16°.

This paper represents the experimental study of hybrid turbine. This hybrid turbine system has a number of potential advantages oven a conventional wind turbine. The present turbine is integrated with solar cells and piezoelectric crystals comparing to conventional wind turbine and it has been illustrated. The performance results are presented for various cases of different wind velocities, blade angles and for different intervals of day time. The results show that hybrid turbine still produces energy without any rotation during rain, day time. This single turbine is more useful and better than using solar panels, rain energy generators and wind mills individually to extract energy from renewable energy sources.

Bio-mimicry is one of the leading fields of research that has been around since the early ages of science. Aerospace industry, especially, takes most of its design inspiration from the aquatic life. In this paper a breed of flying fish scientifically known as Exocoetidae, Cypselurus Hiraii has been chosen to study. The aerodynamic characteristics of the fish were studied experimentally in a wind tunnel previously, but the plausibility of its design application in the aerospace industry hasn’t been explored yet. Therefore, in the present study the cross-section of the fish in the side view has been traced and its aerodynamic performance as a 2D infinite wing has been examined in ANSYS R15 (FLUENT). The performance of this fish inspired shape has been compared to the properties of conventional aerofoils in terms of coefficient of lift and coefficient of drag.

The work in this paper aims to increase the maximum lift coefficient of the airfoil by implementing the co-flow jet concept on NACA 0018 airfoil and also to investigate the performance of co-flow jet (CFJ) airfoil. To conduct numerical solution, RANS equations have been solved for 2D incompressible and unsteady flow using the Spalart-Allmaras turbulence model. The suction surface of the airfoil is modified by placing the injection slot near the leading edge and the suction slot near the trailing edge. A small mass of air is withdrawn into the airfoil suction slot, pressurized by a pumping system located inside the airfoil, and re-injecting into the injection slot tangentially to the main stream flow. The CFJ airfoil is enhancing the aerodynamic lift coefficient significantly compare to the baseline airfoil. And also, the numerical analysis is carried out to investigate the effect of the location of injection and suction slot. And it is observed that the aerodynamic lift coefficient of CFJ airfoil is increasing with varying the injection slot away from the leading edge.

The results of a comparative study on the reduction of broadband noise for several combinations of a flat plate with serrations encountering a low-turbulence fluid flow are computed and documented. The four combinations under study are triangular serrations on leading-edge only, triangular serrations on trailing-edge only, triangular serrations on the leading and trailing edges, and ogival serrations on the leading and trailing edges. Serrations based on the trailing edge are normalized in terms of its chord length. A computational study was carried out using computational fluid dynamics models to simulate the variety of serrated flat plates. Commercial computational fluid dynamics software ANSYS Fluent 16.0 was used. A quantifiable reduction in the broadband noise was found in most of the variations in the serrated geometries. The particular case of the serrations considered in the present study having triangular serrations on both leading and trailing edges of the flat plate proved to be the most effective in terms of broadband noise reduction.

In the present study, an innovative concept of axial flapping wing model is analysed to study and improve the aerodynamic efficiency for vertical takeoff microaerial vehicle. The flapping kinematics are inspired by merging aquatic jellyfish locomotion, and umbrella’s in and out mechanisms with the flappers hinged around a central hub. Also, additional flappers are placed beneath the primary flappers at varied distances. The analysis is performed using FLUENT to study the effect of placing axial flappers that maximize the lift/drag ratio. The chord length of the primary flappers is fixed at 10 cm, and axial flappers at 5 cm as the model needs to be constrained according to DARPA regulations of 15cm. The flapping kinematics are chosen as inward, outward, and symmetrical based on the feasibility of flapping in the axial direction to produce the airflow for generating lift in the vertical direction. The amplitude of the flappers is set at 30° to have a comparative study of other kinematics. The flow structures developed by the interactions of vortices of flapping wings influence the aerodynamic characteristics of the model. The velocity and vorticity magnitude of the flappers are studied and analysed in detail to understand the mechanism of axial flappers in providing better lift/drag ratio. The effect of adding additional flappers underneath the primary flapper model under inwards kinematics was better than primary flapper (Model 0) which significantly increased the aerodynamic performance of axial flapper’s inter-distance variations at 5 cm by 18.3% (Model 1), at 10 cm by 15.2% (Model 2) and at 15 cm by 10.5% (Model 3). The outward and symmetric kinematics models exhibit a decrease in aerodynamic efficiency compared to inward kinematic models.