Design and Drag Analysis of Fixed Wing Unmanned Aerial Vehicle for High Lift

Present work deals with design and analysis of fixed wing aircraft model. Dimensions of aircraft are evaluated considering different factors as weight to be lifted, velocity of aircraft and cruising altitude. Using AIAA rulebook the dimensions of aircraft are fixed. Further the theoretical analysis has been carried out using classical equations for evaluating drag co-efficient with respect to angle of attack and lift co-efficient. The airfoil selection has been carried out by comparing the characteristics of co-efficient of lift, drag and their behaviour against angle of attack for a range of 1ï‚° to 10ï‚°. Using the theoretical outcomes the behaviour of entire aircraft was observed. Simulation of the aircraft has been carried out using XFLR5 software. The theoretical and simulation outcomes are observed to follow similar pattern for co-efficient of drag against both angle of attack and lift co-efficient. Close correlation has been observed between theoretical and simulation results. Present paper presents a design and analysis validation process for aircrafts used in surveillance applications.