The generation of a fully turbulent boundary layerprofile is investigated using analytical andnumerical methods over the Reynolds number range 422≤ Reθ ≤ 31,000. The numerical method usesa new mixing length blending function. Thepredictions are validated against reference windtunnel measurements under zero streamwise pressuregradient. The methods are then tested for low andmoderate adverse pressure gradients. Comparisonagainst experiment and DNS data show a goodpredictive ability under zero pressure gradient andmoderate adverse pressure gradient, with bothmethods providing a complete velocity profilethrough the viscous sub-layer down to the wall.These methods are useful computational fluid dynamictools for generating an equilibrium thick turbulentboundary layer at the computational domaininflow.

Experimental aerodynamic testing of objects in closeground proximity at high subsonic Mach numbers isdifficult due to the construction of a transonicmoving ground being largely unfeasible. Two simple,passive methods have been evaluated for theirsuitability for such testing in a small blowdownwind tunnel: an elevated ground plane, and asymmetry (or mirror-image) approach. The methodswere examined using an unswept wing of RAE2822section, with experiments and Reynolds-AveragedNavier Stokes CFD used synergistically to determinethe relative merits of the techniques. The symmetrymethod was found to be a superior approximation of amoving ground in all cases, with mild discrepanciesobserved only at the lowest ground clearance. Theelevated ground plane was generally found toinfluence the oncoming flow and distort theflowfield between the wing and ground, such that themethod provided a less-satisfactory match to movingground simulations compared to the symmetrytechnique.

In this paper, helicopter rotor blades are analysed inhover using computational fluid dynamics (CFD)coupled with a structural model. The method relieson a mesh deformation algorithm that allows forexchange of forces and deformations between abeam-based finite-element model and the fluid flowvolume mesh. The method is demonstrated againstexperimental data, and the aerodynamic predictionsappear to improve when the aeroelastic model isused. For all employed cases the flexibility of themethod allows the CFD mesh deformation to be spreadover the computational domain in a controlledfashion. The influence of the aeroelasticdeformations on the blade loads was limited yetevident on the rotor performance. The lack ofadequate test cases and experiments for validationof CFD/CSD methods is also highlighted.

The alleviation of gusts effects on a tiltrotor inaeroplane and helicopter operation modes obtained byan optimal control methodology based on theactuation of elevators, wing flaperons andswashplate is examined. An optimal observer forstate estimate is included in the compensatorsynthesis, with the Kalman-Bucy filter applied inthe presence of stochastic noise. Tiltrotor dynamicsis simulated through an aeroelastic model thatcouples rigid-body motion with wing and proprotorstructural dynamics. An extensive numericalinvestigation examines effectiveness and robustnessof the applied control procedure, taking intoaccount the action of both deterministic andstochastic vertical gusts. In addition, a passivepilot model is included in the aeroelastic loop andthe corresponding effects on uncontrolled andcontrolled gust response are analysed.

A robust and efficient computational model has beendeveloped which is capable of modelling the dynamicnon-linear behaviour of Glare panels subjected toblast loadings. High strain rate materialcharacterisation and modelling of interfacialdebonding between adjacent sublaminates have beentaken into consideration. Numerical model validationhave been performed considering case studies ofGlare panels subjected to a blast-type pressurepulse for which experimental data on the back face-displacement and post-damage observations wereavailable. Excellent agreement of mid-pointdeflections and evidence of severe yield linedeformation were shown and discussed against theperformed blast tests. A further parametric studyidentified Glare as a potential blast attenuatingstructure, exhibiting superior blast potentialagainst monolithic aluminium plates. The resultswere normalised and showed that for a given impulse,Glare exhibited a smaller normalised displacement,outperforming monolithic Aluminium 2024-T3 plates.It was concluded that further work needed to becarried out to take into account the influence ofgeometry (cylindrical structures),pre-pressurisation effects and boundaryconditions