Design and Aerodynamic Performance Evaluation of an Open-Circuit Subsonic Wind Tunnel Using Computational Fluid Dynamics
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Computational Fluid Dynamics, Contraction Cone Configurations, Diffuser Configuration, Pressure Recovery Coefficient, Turbulent Intensity, Aerodynamics Performance
Abstract
This study provides an assessment of the design and aerodynamic performance of an open-circuit subsonic wind tunnel using computational fluid dynamics. Eight wind tunnel configurations have been designed, combining two contraction geometries (curved and straight tapered), two diffuser angles (6 and 7 degrees), and two diffuser designs (conventional diffuser and square to circular transition diffuser). The aerodynamic performance of each model was evaluated by means of pressure distribution, speed distribution, turbulence intensity, and the pressure recovery coefficient. The results of the simulation showed that all configurations had successfully accelerated the airflow to a target speed of approximately 30 m/s in the test section. However, significant differences were observed in the performance of the diffuser and the quality of the downstream flow. Models incorporating a square-to-circle transition diffuser showed smoother pressure recovery, more uniform speed gradients, and significantly lower turbulence intensities than conventional diffuser models. These configurations also achieved higher pressure recovery coefficients of (0.65-0.68), which suggests that dynamic pressure conversion is more efficient and that aerodynamic losses are reduced. Although model 2 had the highest-pressure recovery coefficient (0.72), it produced significantly more turbulence downstream of the diffuser. On the other hand, model 6, consisting of a curved deflector, a square-to-circular transition diffuser, and a 6-degree diffuser angle, provided the most balanced aerodynamic performance, combining high pressure recovery, stable speed distribution, and low turbulence. The findings show that optimization of both the contraction and diffuser geometry significantly improves the flow quality of the wind tunnel and provides practical design guidance for the development of efficient open-circuit subsonic wind tunnel aerodynamic testing at the laboratory scale.
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References
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