The symbol of the Hessian for an aeroelastic optimization model problem is analyzed. The ow is modeled by the small-disturbance full potential equation and the structure is modeled by an isotropic (von K arm an) plate equation. The cost function consists of both aerodynamic and structural terms. In the new analysis the symbol of the cost function Hessian near the minimum is computed. The result...

Computational fluid dynamic (CFD) models are ubiquitous in aerodynamic design. Variable-fidelity optimization algorithms have proven to be computationally efficient and therefore suitable to reduce high CPU-cost related to the design process solely based on accurate CFD models. A convenient way of constructing the variable-fidelity models is by using the high-fidelity solver, but with a varying...

TO IMPROVE the aerodynamic performance and the economic benefits of an aircraft engine, one strives to increase the total pressure ratio, the adiabatic efficiency et al., and decrease the size and weight of the engine. Multi-objective optimization has been proposed and studied to satisfy the higher-level requirements in recent years. Benini [1] successfully performed the multi-objective optimiz...

Aerodynamic drag force breakdown of a typical transport aircraft shows that lift-induced drag can amount to as much as 40% of total drag at cruise conditions and 80-90% of the total drag in take-off configuration. One way of reducing lift-induced drag is by using wing-tip devices. By applying several types of winglets, which are already used on commercial airplanes, we study their influence on ...

ABSTRACT: An approximate approach for the frequencyand time-domain aeroelastic analysis of bridge decks is presented. The aerodynamic transfer functions are approximated as a linear function with the coefficients determined through minimization of the weighted error between the exact and approximated transfer function. The weighting function in optimization is introduced for the improved approx...

In this paper, topology optimisation is applied to the design of the rear fuselage of an unmanned aerial vehicle (UAV). A comparison is drawn between the performance of a design created through evolutionary structural optimisation (ESO) and a baseline design modelled on a manually designed and successfully flow fuselage geometry, for different wing shapes. The loading for each wing shape is det...