STEADY STATE AERODYNAMIC ANALYSIS OF （稳态气动分析）.pdf

ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR) Volume 2, Issue 8, August 2013 STEADY STATE AERODYNAMIC ANALYSIS OF AIRCRAFT WINGS WITH CONSTANT AND VARYING CROSS SECTION [1] Jaimon Dennis Quadros, [2] Dr D L Prabhakara Abstract- The flight of an aircraft is mainly generated by Lift force and Drag force. These forces alter the relative wind producing aerodynamic forces that act on the wings of an aircraft. The present paper aims at computing the Co-efficients of Lift and Drag for a typical wing planform of Constant and Varying cross section. Numerical studies are performed to investigate the aerodynamic performance of a thin wing planform having a Constant and Varying Cross- section. The vortex lattice method (VLM) is utilized to simulate the Aerodynamic characteristics on the basis of Computational Fluid Dynamics. The performance characteristics that mainly govern the study are Co-efficient of Lift and Co-efficient of Drag. The study also deals with understanding the effect of various factors such as Aspect Ratio, Sweep angle, Vortex or Panel formation, Taper ratio, Ground Proximity and Dihedral Angle on Aerodynamic characteristics and also decide the wing Fig.1: Aerodynamic load distribution for a dimensions for different wing configurations under rectangular wing in subsonic airstream. Ste