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首页> 外文会议>International Forum on Aeroelasticity and Structural Dynamics >INVESTIGATION OF LOADING PARAMETERS OF A TRUNK-ROUTE AIRPLANE WING IN A WIND TUNNEL NEAR TO BUFFET BOUNDARY
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INVESTIGATION OF LOADING PARAMETERS OF A TRUNK-ROUTE AIRPLANE WING IN A WIND TUNNEL NEAR TO BUFFET BOUNDARY

机译：靠近自助边界的风隧道中继线飞机翼装载参数的研究

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摘要

In the process of design parameters selection of the aircraft have problems to find a balance between the often conflicting set of requirements and limitations. One such problems is to achieve high lift-to-drag ratio and a high cruising speed, while ensuring an adequate supply to the of buffeting boundary and loss of stability and controllability. In this regard, there are problems of choice of optimal contours of the airframe to ensure high efficiency of the aircraft, the performance of designated limits and providing reserves to the parameters. Reservs must meet the regulatory requirements for the chosen geometric parameters of the aircraft. The lift coefficient of buffet onset (CLbuff) or boundaries buffeting is one of those limitations that must be considered when creating a subsonic aerodynamic design of the wing aircraft, starting from the stage of its conceptual design. When cruising (transonic) Mach numbers pressure pulsations, creating bafting load, due to the interaction of shocks and the boundary layer of the wing. These pulsations are associated with fluctuations in flow separation zones, positions and intensities of shocks. The investigations model swept wings of high aspect ratio are carried out. The measurements of the pressure, pressure oscillation in control points located on the upper surface of the wing model by means multichannel information-measuring systems are fulfilled. Tests were carried out in the presence or absence of baffles, located near the leading edge of the wing (for fixing the area of the laminar-turbulent transition) at subsonic and transonic flow regimes. The influence of the angle of attack, Mach and Reynolds numbers on nonstationary characteristics was researched. Tests were carried out in the free stream wind tunnel (without additional sources of disturbances in the form of turbulence-mesh oscillating grids, etc.). The buffet boundaries the angle of attack using several different criteria are defined.
机译：在设计参数的过程中，飞机的选择有问题，可以在经常相互冲突的要求和限制之间找到平衡。一个这样的问题是实现高升力比和高巡航速度，同时确保对缓冲边界和稳定性损失和可控性的充分供应。在这方面，存在机身的最佳轮廓选择的问题，以确保飞机的高效率，指定限制的性能和向参数提供储备。备用必须符合飞机所选几何参数的监管要求。自助式发作（Clbuff）或边界的升力系数是在从其概念设计的阶段开始创建机翼飞机的亚音速空气动力学设计时必须考虑的那些限制之一。当巡航（横向）马赫数压力脉动时，产生锻造载荷，由于冲击的相互作用和机翼的边界层。这些脉动与流动分离区域，位置和冲击强度的波动相关联。进行了高纵横比的调查模型扫过的翅膀。借助于多通道信息测量系统，借助于多通道信息测量系统的控制点的压力，压力振荡的测量值。在围绕机翼的前缘附近的挡板存在或不存在测试中进行测试，用于在亚音速和跨音速流动状态下固定层压湍流过渡的区域。研究了攻击角度，马赫和雷诺数对非间平特征的影响。在自由流风隧道中进行测试（没有湍流 - 网格振荡网格的形式的额外扰动源。自助式边界使用几种不同标准进行攻击角度。

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