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There is increasing concern about potential differences in aerodynamic behavior measured in steady flow wind tunnel conditions and that which occurs for vehicles on the road. As tools become available for better simulation of on road conditions there is a growing practical value in understanding what range of conditions are important to simulate. Surface pressures measured on the sideglass of a European hatchback vehicle in the MIRA full scale wind tunnel are compared with those measured on-road. The on-road data corresponds to relatively calm, low yaw conditions and the time averaged pressure distributions on-road and in the wind tunnel at zero yaw were very similar. Variations in instantaneous aerodynamic yaw angle produces fluctuations in surface pressures but the sensitivity of instantaneous pressures to yaw angle was lower for the on-road measurements compared with steady state wind tunnel tests.

The aerodynamic development and evaluation of passenger vehicles is almost universally performed in the controlled, low turbulence environment of a wind tunnel or under similarly idealized conditions using CFD. This environment is substantially different from that which is experienced on-road due to the effects of atmospheric winds and the wake flows from other road vehicles. The scope of this work is to establish, with regard to surface pressures, if a low turbulence wind tunnel evaluation of passenger cars yields results which accurately reproduce on-road data or whether a more complete simulation of the real world is required. The test vehicle was a Rover 214, a typical European mid-sized hatchback. Data were obtained from both the MIRA full-scale wind tunnel and on the road using the same vehicle and instrumentation. The on-road data were gathered under various atmospheric wind conditions.

Water tow-tank tests were performed for the Ahmed model at a range of “high-drag” backlight angles at Reynolds numbers of up to 1.3 × 105. Dye was injected just upstream of the c-pillars and visualizations were recorded with a submerged CCD camera moving with the model. Discrete sub-vortices were found to be shed periodically along the length of the c-pillar at Strouhal numbers (based on square root of frontal area) between 8 and 12. These sub-vortices were observed to undergo vortex pairing and then to roll up into the familiar c-pillar vortices. These observations are consistent with previously published observations for delta wings. Wind tunnel tests were performed in order to provide Reynolds numbers of up to 1.6 × 106. These revealed some spectral features which could be due to the shedding and pairing of discrete vortices from the c-pillar but the evidence was much less conclusive than at low Reynolds number.

The unsteady wake of the Ahmed model has been investigated experimentally using time-accurate 5-hole and hot-wire probes and computationally using Exa PowerFLOW. The backlight angle was 25° which was chosen to be slightly below the critical angle observed computationally. The CFD results are similar to experimental results for backlight angles just below the critical angle (eg: 27.5°, 30°). Unsteady flow-field reconstruction of the experimental results and the CFD results both revealed a quasi-two-dimensional vortex-shedding type structure from the bottom of the model base. This results in a semi-periodic build up and collapse of the near wake and produces a symmetric oscillation in the strength and position of the rear pillar vortices. The period of this phenomenon corresponds to a Strouhal number of approximately 0.5 based on free-stream velocity and the square root of the model frontal area.