ADAPTIVE SHOCK CONTROL BUMPS

自适应减震控制颠簸

基本信息

批准号：
1817443
负责人：
金额：
--
依托单位：
Imperial College London
依托单位国家：
英国
项目类别：
Studentship
财政年份：
2016
资助国家：
英国
起止时间：
2016 至无数据
项目状态：
已结题

来源：
https://gtr.ukri.org/projects?ref=studentship-1817443
关键词：
ADAPTIVE SHOCK CONTROL BUMPS

项目摘要

The rising demand for air travel requires the engineering community to improve the aerodynamic efficiency of aircraft, especially in the context of tightening emission regulations such as the Vision 2020 directive. The plateau reached in the refinement of airframe technology in the last few decades has shifted the research focus on flow control devices such as shock control bumps (SCBs). Other flow control techniques include variable camber aerofoils, or the use of suction and vortex generators, but, as the two EUROSHOCK programs have highlighted, shock control bumps are one of the most promising shock control systems (Stanewsky et al. 1997, Stanewsky et al. 2002).Shock control bumps have the potential to improve the performance of transonic wings through the manipulation of the airflow over the suction surface. They generally take the form of small local deformations consisting of a ramp upstream of the nominal location of the normal shock wave, which generates near-isentropic compression waves and bifurcates the normal shock, followed by a tail, which brings the flow back to the aerofoil surface (Bruce and Colliss 2014). Shock control bumps can either be 2D or 3D. In the first case, the bump profile is constant along the span; in the second, several bumps are placed along the wing.One of the main issues associated with (both 2D and 3D) shock control bumps is that the beneficial smearing effects and stagnation pressure savings achieved at design are accompanied by an increase in drag off-design, when the position of the shock wave relative to the bump crest has changed.

对航空旅行的需求不断上升，要求工程界提高飞机的空气动力学效率，尤其是在收紧排放法规（例如2020 Vision 2020指令）的背景下。在过去的几十年中，机身技术的完善中达到了高原，这使研究重点关注流控制设备，例如冲击控制颠簸（SCB）。 Other flow control techniques include variable camber aerofoils, or the use of suction and vortex generators, but, as the two EUROSHOCK programs have highlighted, shock control bumps are one of the most promising shock control systems (Stanewsky et al. 1997, Stanewsky et al. 2002).Shock control bumps have the potential to improve the performance of transonic wings through the manipulation of the airflow over the suction surface.他们通常采用小型局部变形的形式，该变形由正常冲击波的标称位置的坡道组成，该坡道会产生近乎凝集的压缩波，并分叉正常冲击，然后尾尾，将流动回到气压表面（Bruce and Colliss 2014）。冲击控制颠簸可以是2D或3D。在第一种情况下，凸起曲线沿跨度是恒定的。在第二个上，沿翼沿几个颠簸放置。与（2D和3D）冲击控制颠簸相关的主要问题之一是，当设计时所获得的有益的涂抹效果和滞留压力均伴随着拖动偏置的增强，而相对于颠簸波峰的位置发生了变化。