This thesis presents the simulation analysis carried out for the wing of the USM EUAV. The main objective is to generate the aerodynamics characteristics data of the wing using the CFD which will be used to calculate the longitudinal stability coefficients and derivatives of the USM E-UAV. The simulation was carried out by using ANSYS FLUENT where the lift and drag coefficients were generated at different angles of attack. The virtual environment of the simulation was simulating as a free flow in the open air. A hybrid mesh generation method was used to generate the mesh of the domain and wing. Types of elements that involve are tetrahedron, prism, pyramid and hexahedron. Total of 78 000 of nodes and 400 000 of elements were included to build the mesh of the domain and wing. For the solution model of the simulation, the Spalart-Allmaras turbulence viscosity had been chose since the boundary condition of the simulation is consider as simple and subsonic which is 40m/s. In this study, the Mach number is 0.12 with the air density of 1.225 kg/m3, temperature of 288 k and Reynolds number of 1. 808x106. As for the coefficient of moment of the wing contribution, it will be determined through numerical method. Afterward, the dimensionless lift and drag coefficients at different angles of attack gather from the CFD model will then validated using published calibrated lift and drag coefficients evident in the literature. Thereafter these data will be input into the numerical calculation of the longitudinal stability coefficients and derivatives.
Cfd-based wing aerodynamics and stability analysis of the usm e-uav_Tan Hock Shen_A2_2012_NI