Design optimization of rotor propulsive delta wing

Abstract

The Wing Rotor Configuration is designed for the purpose of VTOL (vertical takeoff and landing) which is a combination of Delta wing and rotor together integrated at the empennage section of the aircraft wing. The model of the delta wing rotor configuration will be modelled by using the solid works part modelling software, later the model will be studied in cfd to understand the aerodynamic performance of the aircraft. The objective of the work is to achieve high aerodynamic efficiency of the chosen configuration. The model analysis includes static and CFD analysis where flow analysis is the primary function, deflection and stress distribution is calculated in the static analysis in ansys static structural module and velocity streamlines and pressure distribution is calculated in the flow analysis which is done using the CFD module of ansys software , major applications include VTOL of different aircrafts [majorly UAV’S (unmanned aerial vehicle), MAV’S (micro aerial vehicle), and fighter aircrafts.