Paper Contents
Abstract
The main aim of this project is to embed the engine in wing. So that the profile drag will be reduced and to determine the flow field of the wing. The idea behind the concepts is to fully integrate a propulsion system within a wing structure so that the aircraft takes full benefits of coupling of wing aerodynamics and the propulsion thrust stream. The objective of this study is to assess the feasibility of the EWP concept applied to large transport aircraft such as the Blended-Wing Body aircraft. In this paper, some of early analysis and current status of the study are presented. In addition, other current activities of distributed propulsion under the RAC project are briefly discussed. We NACA 0012 Which is the airfoil and has a needed thickness. NACA 0012 airfoil is drawn using GAMBIT and then a cut for coefficient of lift, in FLUENT FOR Various angle of attack. And then a cut section is made in the trailing edge, it is analyzed for coefficient of lift. A graph is drawn between coefficients of lift Vs angle of attack, in comparison with experimental data. Later a jet is introduced in trailing edge, and it is analysed for various, and Vorticity magnitude is determined. Later in hot jet various jet temperatures is applied, for that, magnitude and temperature flow is analyzed.
Copyright
Copyright © 2025 SIVA JOTHI S. This is an open access article distributed under the Creative Commons Attribution License.
