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In October 1985, a new wind tunnel was completed and put into operation at the Nissan Technical Center. This paper describes its main specifications and performance features, and gives results of a number of experiments using the new facility. It is a closed-circuit wind tunnel of the so-called Göttingen type, with a semi-open test section. The test section is equipped with two different nozzles, which are used interchangeably depending on the type of testing being carried out. The larger nozzle has a maximum wind velocity of 190 kmh, and a cross-section 4 m high by 7 m wide. The other is 3 m high by 5 m wide and has a maximum wind velocity of 270 kmh. All of the testing equipment in the tunnel, including the axial-flow fan, six-component aerodynamic balance, and traverse system, are operated automatically by a control system made up of several computers linked together. The most notable feature of this wind tunnel is the large reduction that has been made in background noise.

This paper presents a swiring flow type jet pump which has been developed and in put into practical use in transferring fuel between sumps in saddle-shaped fuel tanks. The pump is driven by the force of excess fuel returning from the engine. The major structural features of the pump are described along with its performance. Various problems encountered in the process of developing the pump are discussed along with the technologies developed to resolve them. Particular attention is focused on the effects that the geometries if the nozzle, throat and swirling groove have on fuel transfer efficiency. The results of experiments carried out to analyze these correlations are also presented.

This paper describes the numerical and experimental approaches that were applied to study swirl injectors that are widely used in direct-injection gasoline engines. As the numerical approach, the fuel and air flow inside an injector was first analyzed by using a two-phase flow analysis method [VOF (Volume of Fluid) model]. A time-series analysis was made of the flow though the injector and also of the air cavity that forms at the nozzle and influences fuel atomization. The calculated results made clear the process from initial spray formation to liquid film formation. Spray droplet formation was then analyzed with the synthesized spheroid particle (SSP) method. As the experimental approach, in order to measure the cavity factor that represents the liquid film thickness, nozzle exit flow velocities were measured by particle image velocimetry (PIV).