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reverser considered in this paper uses the natural blockage concept, with only the fan duct flow being reversed. This paper focuses on the study of the aerodynamic performance of the cascade within a cold stream thrust reverser. Aerodynamic simulations are carried out using realistic operating conditions, for idealized cascade models representing three design options. The aim of this work is to investigate whether the aerodynamic performance of the thrust reverser cascade has been improved while minimizing weight of the cascade. In addition, t1his is the first attempt of us to considering noise reduction during design of the thrust reverse. The numerical simulations show that despite a reduction in total reverse thrust for the weight reduced designs, the supersonic flow regime, which existed in the original design, was eliminated after changing vane configurations made with the 5% and 10% weight reductions. The aerodynamic performance around the cascade and in the fan duct within the thrust reverser has been improved. Moreover, the acoustic characteristics of the thrust reverser are improved too. The total reverse thrust is not significantly affected with the modified cascade.

THE thrust reverser is a powerplant component subject to equally fundamental demands by both the engine and airframe and as such represents an Airframe/Propulsion interface topic. Since it makes a significant contribution to DOC, primarily by its capital cost and weight which may typically be some 16% and 18% of a current fan engine powerplant respectively, there is a requirement to develop comprehensive criteria for safety, performance and cost effectiveness assessment. This requirement has always existed but has been submerged by the need to place effort on components which have yielded a more readily identifiable return. The need to economise on both financial and energy resources is resulting in closer attention to powerplant total compatibility and an increasing effort on reverser installation is required.

Outlines some of the features and design issues surrounding the thrust reverser actuation system (TRAS).

Costly physical experiments are normally used to evaluate the performance of thrust reverser concepts during the design process. This is because the design geometry is normally so complex that producing a computational fluid dynamics (CFD) model would take longer than running an experiment. Recently, unstructured grid CFD software packages have come onto the market that claim to greatly reduce the amount of time required to produce a grid. One of these packages. RAMPANT from Fluent, Inc., Lebanon, New Hampshire, was used to model an experimental thrust reverser design. A series of varying cascade blades were modelled in less than a day and the analysis results matched well with the experimental data.

AS aircraft become larger and heavier and their landing speeds increase so the problem of stopping them within a required distance under a range of specified conditions becomes acute. As far as military aircraft are concerned, every technical trick of the trade can be used such as large area flaps, airbrakes, double‐disk hydraulic wheel brakes with anti‐skid units, tail parachutes and even runway mounted arrester units.

CF6–50A engines have been selected to power the European A300B aircraft scheduled for certification and airline delivery in 1974.

AS befitting the occasion of its Silver Jubilee, the twenty‐fifth Paris International Air Show was indeed the most comprehensive yet staged. Nearly 700,000 people visited the Show during its eleven day run, and the International Flying Display on the final day drew an estimated 300,000. Close on 400 different types of aircraft were demonstrated in the air and on the ground, and a multitude of projects were illustrated on the stands of the Indoor Exhibition varying from Mach 3 supersonic transports to one‐man helicopters.

Our report on the Paris Air Show takes the form of an introduction, information on highlights and an overall impression of what is thought to be of most interest to our readership.