Aeroelastic Analysis of Flying Wing Aircrafts

Please enable javascript in your browser.

Joulaei, Mohammad Moin | 2017

1080 Viewed

Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 49896 (48)
University: Sharif University of Technology
Department: Air Structures
Advisor(s): Dehghan Firouzabadi, Rouhollah; Haddadpour, Hassan
Abstract:
Purpose of this thesis is to discover the governing equation of Flying Wing aircrafts. In Flying Wing aircrafts crew, payload, fuel, and equipment are typically housed inside the main wing structure. A clean flying wing is sometimes presented as theoretically the most aerodynamically efficient (lowest drag) design configuration for a fixed wing aircraft. We assume Flying wing as plate. Achieve structural formulation needs to use modal deflections and put them in Lagrangian equations. In the right had side, pressure on flying wing can be found. To obtain air pressure on flying wing in this thesis, applying Quasi steady aerodynamic and Howe distribution is necessary. Applying this method on flying wing models and analyze them is achieved in this thesis
Keywords:
Modal Analysis ; Quasi Steady Aerodynamics ; Flying Wings ; Motion Lagrange Equations ; Stability Analysis ; Delta Wing ; Pressure Distribution