Four well known shape parameterization techniques were considered for study Bezier curves, Class-Shape function Transformation, Hicks-Henne " Bump " function and polynomial method. This paper investigates the effect of shape parameterization on an automated aerofoil shape optimization problem. The selection of suitable shape parameterization technique is one of the significant factors affecting the fidelity of the solution found during aerofoil shape optimization process. The 40 % truncated nozzle is found to give optimum performance and it has achieved the desired exit Mach number in all the three altitude conditions. The results show that the flow pattern of the nozzles under different altitude conditions are almost similar. Optimum percentage of the truncation is selected by the comparison of nozzles with different lengths of truncation under various altitude parameters. The flow-fields obtained through the numerical simulation are analysed to know the effect of truncation on the performance of aerospike nozzle. FLUENT predictions were used to verify the isentropic flow assumption and that the working fluid reached the design exit Mach number. Simulation of the flow is carried out at three different altitude conditions representing Under-expansion, Ideal, and over-expansion conditions of the flow. For this purpose nozzles with truncation lengths of 25%, 40%, 50% are choosen, because of the thermal and structural complications in the ideal aerospike nozzle. This paper presents the design of aerospike nozzles using characteristic method in conjunction with streamline function, and performance study through numerical simulation using commercial Computational Fluid Dynamics (CFD) code ANSYS FLUENT. To validate the strength of the propeller, Structural and buckling analysis is performed.Īerospike nozzles are being considered in the development of the Single Stage to Orbit launching vehicles because of their prominent features and altitude compensating characteristics. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. By adding this auxiliary equipment the weight of propeller are significantly increased. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 0 0, 10 0 and 20 0 and to determine the drag and lift coefficients by applying inlet velocities. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The design profile chosen is based upon existing literature studies. The objective is to improve the stability of the airfoil when the flow approaches transonic Mach speeds. The main goal of the proposed paper is to carryout the simulation and analysis of RAE 2822 supercritical airfoil with and without wedge profiles along with the study of aerodynamic characteristics such as Lift and drag coefficients at different Mach numbers. The flow properties such as pressure, temperature and density experience a drastic change upstream and downstream of the generated shock. This shock wave is a type of propagating disturbance which greatly effects the aerodynamic performance of the airfoil. The formation of a shock wave is observed when the free stream approaches a transonic mach number. The present work emphasizes the computation of a supercritical airfoil with and without wedge profiles at different angles of attack and free stream velocities. This led to design changes and optimization of the foil with the help of a cusp like structure added to the trailing edge of the foil. A distinctive supercritical airfoil is found to give inappropriate results at peak operating conditions. The Aerodynamic characteristics of an airfoil play a very important role in terms of design aspects and experimental validation.
0 Comments
Leave a Reply. |