Steady state aerodynamic analysis of aeroplane wings with constant and varying cross section

Author

Quadros, Jaimon Dennis ; Prabhakara, D.L.

Author_Institution

Sahyadri Coll. of Eng. & Manage., Mangalore, India

fYear

2013

fDate

27-28 Sept. 2013

Firstpage

1

Lastpage

7

Abstract

This paper presents a FORTRAN program for estimating aerodynamic characteristics of a wing planform of constant and varying cross-section of an aeroplane using Vortex Lattice Method (VLM). The Aerodynamic characteristics of interest are Lift, Drag acting on different parts of the wing. The program was developed to understand the effect of various parameters such as Aspect Ratio (AR), Sweep Back angle, Vortex or Panel formation and ground proximity on Lift and Drag and also to decide the wing dimensions for different wing configurations under Steady Subsonic flow. The results were obtained for a wing planform with rectangular Cross section with a specified Aspect Ratio. The theoretical results for Lift, Drag are computed using VLM. The obtained theoretical results are compared with the experimental results.

Keywords

FORTRAN; aerodynamics; aerospace components; aerospace engineering; aircraft; computational fluid dynamics; drag; lattice theory; mechanical engineering computing; subsonic flow; vortices; AR; FORTRAN program; VLM; aerodynamic characteristics; aeroplane wings; aspect ratio; constant cross-section; drag; ground proximity; lift; panel formation; rectangular cross section; steady state aerodynamic analysis; steady subsonic flow; sweep back angle; varying cross-section; vortex lattice method; wing configurations; wing dimensions; wing planform; Drag; Lift; Vortex Lattice Method;

fLanguage

English

Publisher

iet

Conference_Titel

Research & Technology in the Coming Decades (CRT 2013), National Conference on Challenges in

Conference_Location

Ujire

Electronic_ISBN

978-1-84919-868-4

Type

conf

DOI

10.1049/cp.2013.2533

Filename

6851580