Publication

Abstract : The present work aims to develop an efficient numerical tool that helps create a reliable propulsion system for the micro wing structures used in micro air vehicles. It will in turn enhance the Martian exploration rate of these vehicles during their flight. The biosphere changes are unexpected during many subsonic compressible flows. An optimized shape of these rotary wings can reduce the effects caused by detached flows on the airfoil, subsonic compressible flows, and many other environmental variations. The modified design of the rotor airfoils used in micro air vehicles are essential for the better lift and minimized drag. The stability of the airfoil needs to be maintained for a longer period for many widespread processes. To carry out the effective performance of MAVs an optimized shape of the rotor wings must be designed considering all parameters of aerodynamic structure. To increase the performance and endurance of micro air vehicles the aerodynamic parameters and its analysis has been carried out in the present work for Reynolds number 1000 for NACA 0012. Shaping airfoils for micro air vehicles is required for their better lift and efficient performance in military purposes are presently in great demand. The precise detection of aerodynamic characteristics by the finite element meshing technique is advantageous for the appropriate selections of suitable airfoils utilized in such vehicles. The innovative concept of subparametric higher order meshing technique implemented over the airfoils has been adopted for the present precise evaluation.