声学风洞的设计与仿真

Design and Simulation of Aeroacoustic Wind Tunnel

声学风洞优化设计问题随着航空交通运输业的发展,飞机产生的噪声问题日益引起人们的重视。为此,对地面实验设备就提出更高的要求,开展了航空声学风洞的研究。针对传统声学风洞靠经验和工程估算的设计方法准确性差的问题,提出采用数值仿真的方法对将要建造的声学风洞内流场进行建模仿真。得到给定速度下,得到风洞整体内流场的速度及压力分布,比较了风洞各段的压力损失系数和轴线的速度分布,并结合气动声学FW-H方法给出了各段的声压级。结果表明,通过数值仿真可对风洞前期优化设计起到指导作用。

Aeroacoustic wind tunnel is an important experimental facility in the laboratory to study the noises caused by aircraft. At present, the engineering experience and estimation based on conventions to simulate the flow field in aeroacoustic wind tunnel can not depict exactly part or unitary flow field. Thus this paper simulated the flow field in aeroacoustic wind tunnel which is going to be built through numerical simulation method. Also, under some key velocities of wind tunnel, the study obtained the velocity and pressure distribution on different sections of the wind tunnel. Then, the pressure loss coefficients and axis velocities of different sections were compared. Finally, aeroacoustie FW - H method was employed to calculate the sound pressure level. The result shows that it is beneficial for wind tunnel design in earlier stage.