The contemporary approach to helicopter mathematical modelling in simulation for handling qualities applications is to represent each blade individually. This allows incorporation of effects not possible with a multiblade disc representation of the rotor system. This paper addresses the validation of such a model, which is uniquely performed for large amplitude manoeuvres, using a recently-developed approach to inverse simulation. The method is reviewed in the context of model validation, and comparisons between simulation and actual data are presented for a Puma helicopter executing sidestep manoeuvres in low-speed flight. The focus for interpreting the results is in the area of wake modelling. It is concluded that further developments are necessary in this area if helicopter flight mechanics models are to be used in simulation of role-related flight.

The computation of slowly moving Shockwaves is considered. A numerical error is introduced into the solution during an explicit computation, which results in the generation of spurious entropy. The generation of this spurious entropy and its effect on the pressure wave in Euler flows is examined, in one dimension by considering a moving shock in a constant area duct, and in two dimensions by considering an unsteady aerofoil flow. An efficient temporal discretisation is presented, whose advantages over the explicit scheme are two-fold. First, the numerical entropy generation due to shock motion is eliminated, and second, the CPU requirements for a two-dimensional unsteady computation are reduced by a factor of five from that required for the explicit scheme, for no loss of accuracy.

The work reported here was an experimental study of the combined influence of a sandpaper rough surface and a stream turbulence upon laminar and transitional boundary layers. Data correlations were obtained using the previously determined parameter of an equivalent Nikuradse size of roughness. These correlations are derived for the development of the laminar layer in thickness and profile shape factor, for the onset and the length of transition and for the distribution of intermittency through transition. Further fundamental differences in flow behaviour from those in a rough pipe have been found to add to those already reported.

An expression is derived to predict the effect of taper ratio on the vortex drag of high aspect ratio, unswept, planar wings. The expression was formulated by assuming that imposing an elliptic spanwise load distribution on the tapered planform, would result in a leading edge thrust excess, which relates to the increase in vortex drag above the theoretical minimum. Comparisons of this expression with results from lifting line theory show encouraging agreement.

Since 1993, research at Loughborough University has included examining the commercial air safety record of Australia in an attempt to rise to the challenge posed by Professor James Reason: “Should we not be studying what makes organisations relatively safe rather than focusing upon their moments of unsafety? Would it not be a good idea to try and find out what makes them good and whether or not these ingredients could be bottled and handed on?”.

The objective is not to prove Australia to be the safest place to fly, nor its airlines the safest in the world. It is simply to examine what sort of defences are in place that may be strengthened or emulated.

The problem of designing a composite laminated plate subject to multiple loading cases is addressed using the methodology of heuristic redesign. Lower bounds on extensional stiffnesses together with a maximum strain first ply failure criterion constitute the design constraints. The general theory of heuristic redesign and its application to this particular problem are described. Results for different combinations of loading cases and redesign strategies are presented.