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The 9-meter wind tunnel of the National Research Council (NRC) of Canada is commonly employed in full-scale testing of class 8 tractors. In this configuration the model blocks 10 - 15% of the test section cross-sectional area, which is greater than generally advocated blockage limits. The NRC utilizes the Maskell III method to correct data for wall interference but the effectiveness of this technique at such blockage levels remained to be seen. Corrected full-scale data was compared to data acquired with a half-scale model to determine how closely the corrected high-blockage data would agree with the low-blockage baseline. The half-scale model presented an opportunity to test at full-scale Reynolds numbers, with less than 4% blockage, which falls within most recommendations of maximum allowable blockage.

Tube drawing is a well known process involving at room temperature the reduction of diameter and wall thickness to obtain specified values. The initial tube is drawn into a die of a smaller opening and its thickness achieved by use of a mandrel. Usually, the mandrel has a land area which diameter defines by sizing the inside diameter of the final tube. Some structural components found in cars, aircrafts and other vehicles require bent or hydroformed tubes of lower weight. It is of interest to have tubes of varying axial or circumferential thickness so that to reduce overweight in low stressed areas and reinforce it otherwise. However, the production of tubes of varying thickness is more difficult in reason notably of higher metal flow stresses in the deformation zone and the need to control precisely the mandrel position during drawing.

This paper examines the aerodynamic behaviour of plane-walled, single-plane-expansion, underbody diffusers fitted to a wind-tunnel model of a wheel-less, simple body having automobile proportions. The measurements were performed over a moving-belt assembly in the Pilot Wind Tunnel of the National Research Council of Canada (NRC). The purposes of the investigation were: to understand the governing physics of automotive underbody diffusers operating in ground proximity, to examine the effect of moving-ground and fixed-ground simulations on the behaviour of such diffusers and on the corresponding vehicle downforce and drag, to map the performance of simple, quasi-two-dimensional diffusers when used to produce downforce or drag reduction.

The usage of aviation turbine fuel in Canadian operations has been the subject of a study sponsored by the Canadian Ministry of Transport. The study was designed to cover all aspects of aircraft operation from ground handling to aircraft in flight and included such parameters as availability and operating costs. Of particular importance was the effect of Canadian climatic conditions on the requirements for aviation turbine fuels for Northern operations. The final report prepared by an engineering consultant was based upon the reports from four sub-groups formed to cover all the aforementioned areas. The final conclusions of the study presented in this paper consider that due to the climatic conditions there is a place for both wide-cut and kerosene fuels in Canadian operations.

This paper outlines the techniques used to install both a full scale and a half scale tractor-trailer model in the 9×9 meter National Research Council of Canada wind tunnel in Ottawa, Canada. The objectives were to measure the cooling drag of an active cooling system and to investigate the aerodynamic testing limits of long, yawed models inside a solid wall wind tunnel. The tunnel interference problem is discussed as it pertains to the upstream boundary, test section floor, downstream boundary, ceiling and side walls and tractor-trailer surface pressure measurements. A potential solution to the problem, however, is the subject of a follow-up paper.

The Enhanced/Synthetic Vision System (E/SVS) is a Technology Demonstrator (TD) project supported by the Chief, Research and Development of the Canadian Department of National Defence. E/SVS displays an augmented visual scene to the pilot that includes three separate image sources: a synthetic computer - generated terrain image; an enhanced visual image from an electro-optical sensor (fused as an inset); and aircraft instrument symbology, all displayed to the pilot on a Helmet Mounted Display (HMD). The synthetic component of the system provides a 40 degree vertical by 80 degree horizontal image of terrain and local features. The enhanced component digitizes imagery from electro-optic sensors and fuses the sensor image as an inset (20 degrees by 25 degrees) within the synthetic image. Symbology can be overlaid in any location within the synthetic field-of-view and may be head, aircraft, target or terrain referenced.

MIT Lincoln Laboratory is tasked by the U.S. Federal Aviation Administration to investigate the use of the NEXRAD polarimetric radars* for the remote sensing of icing conditions hazardous to aircraft. A critical aspect of the investigation concerns validation that has relied upon commercial airline icing pilot reports and a dedicated campaign of in situ flights in winter storms. During the month of February in 2012 and 2013, the Convair-580 aircraft operated by the National Research Council of Canada was used for in situ validation of snowstorm characteristics under simultaneous observation by NEXRAD radars in Cleveland, Ohio and Buffalo, New York. The most anisotropic and easily distinguished winter targets to dual pol radar are ice crystals.