Assessment of Wake-Tail Interference Effects on the Dynamics of Flexible Aircraft
Murua, J, Palacios, R and Graham, JMR (2012) Assessment of Wake-Tail Interference Effects on the Dynamics of Flexible Aircraft AIAA Journal, 50 (7). pp. 1575-1585.
J03@ Murua, Palacios & Graham (AIAAJ, 2012) Assessment of wake-tail interference effects on the dynamics of flexible aircraft.pdf
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This work investigates the effect of aerodynamic interference in the coupled nonlinear aeroelasticity and flight mechanics of flexible lightweight aircraft at low speeds. For that purpose, a geometrically exact composite-beam formulation is used to model the vehicle flexible-body dynamics by means of an intuitive and easily linearizable representation based on the displacement and Cartesian rotation vectors. The aerodynamics are modeled using the unsteady vortex-lattice method, which captures the instantaneous shape of the lifting surfaces and the free inviscid wake, including large deformations and interference effects. This results in a framework for simulation of high aspect ratio planes that provides a medium-fidelity representation of flexible-aircraft dynamics with a modest computational cost. Previous independent studies on the structural-dynamics and aerodynamics modules are complemented here with the integrated simulation methodology, including vehicle trim, and linear and nonlinear time-domain solutions. A numerical investigation is next presented on a simple wing-fuselage-tail configuration, assessing the interference effects between wing wake and horizontal tail, and the downwash due to the proximity of the wake is shown to play a significant role in the longitudinal dynamics of the vehicle. Finally, a brief discussion of direct wake-tail encounters is included to show the limitations of the approach.
|Divisions :||Faculty of Engineering and Physical Sciences > Mechanical Engineering Sciences|
|Date :||1 July 2012|
|Identification Number :||10.2514/1.J051543|
|Uncontrolled Keywords :||Free wake, Aerodynamic interference, Flexible aircraft, Flight dynamics, Aeroelasticiy, Vortex lattice method|
|Additional Information :||Copyright AIAA. This is the final accepted version of an article published in the AIAA Journal 50 (7), July 2012. The published version may be found at: http://dx.doi.org/10.2514/1.J051543|
|Depositing User :||Symplectic Elements|
|Date Deposited :||13 Sep 2013 08:27|
|Last Modified :||23 Sep 2013 20:15|
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