Aeroelastic stability of delta wing configuration

Aravinth, Dinesh and M S, Mahesh (2016) Aeroelastic stability of delta wing configuration. In: 6th International Congress on Computational Mechanics and Simulation, 27 June - 1 July 2016, IIT Bombay, Powai, Maharashtra, India.

Full text not available from this repository. (Request a copy)

Abstract

Mathematical formulation for aeroelastic analysis of low aspect ratio box beam structured delta wing immersed in incompressible flow is analyzed in this paper. An algorithm based on Hamilton’s variational principle and Galerkin approach has been used for the determination of divergence instability of a delta wing structure at high angle of attack. The structural model incorporates non classical effects such as anisotropy. As compared to moderate swept wing, the nonlinear lift terms corresponding to that of vortex lift comes into effect in a highly swept delta wing. Polhamus leading edge suction analogy concept has been used for calculating the nonlinear terms. The box beam structure and Polhamus concept are used together for the formulation of the stability of the fluid structure interaction problem.

[error in script]

IITH Creators:	IITH Creators ORCiD M S, Mahesh UNSPECIFIED
Item Type:	Conference or Workshop Item (Paper)
Subjects:	Physics > Mechanical and aerospace
Divisions:	Department of Mechanical & Aerospace Engineering
Depositing User:	Team Library
Date Deposited:	29 May 2019 08:16
Last Modified:	29 May 2019 08:16
URI:	http://raiithold.iith.ac.in/id/eprint/5373
Publisher URL:
Related URLs:

Actions (login required)

View Item

Statistics for this ePrint Item