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自20世纪60年代Davenport提出钝体气动导纳概念之后,气动导纳一直是钝体空气动力学研究的焦点之一。本文通过大量风洞试验,研究了湍流场中NACA0012翼型和七种典型钝体截面的非定常气动力,试验中首次采用同步脉动压力测量技术,气动导纳的识别采用统计理论。试验得到如下两个主要结论:对于某一给定的几何断面,非定常气动力与湍流各脉动分量存在着不同的气动导纳:流线型体的气动导纳对攻角变化较敏感,而对钝体的影响不太明显。
Since the concept of bluff-body aerodynamic admittance was proposed by Davenport in the 1960s, aerodynamic admittance has been one of the focuses of bluff-body aerodynamics. In this paper, a large number of wind tunnel tests were conducted to study the unsteady aerodynamic forces of NACA0012 airfoil and seven typical bluff body sections in turbulent flow field. The synchronous pulsating pressure measurement technique was used for the first time in the experiment. The statistical theory was adopted to identify the aerodynamic admittance. The main conclusions of the experiment are as follows: The aerodynamic admittance of unsteady aerodynamics and turbulent fluctuating components exists for a given geometric cross-section. The aerodynamic admittance of streamlined bodies is more sensitive to changes of angle of attack, The impact of the body is not obvious.