权益分类	功能权益	普通用户	{{item.name}}会员
{{category.name}}	{{benefitItem.name}}

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.

不断增长的航空旅行需求要求工程界提高飞机的空气动力学效率，特别是在诸如Vision 2020指令等严格排放法规的背景下。在过去几十年中，机体技术的改进达到了一个平台期，这使研究的重点转移到流动控制装置上，如激波控制凸块（SCB）。其他的流动控制技术包括变弯度翼型，或使用吸力和涡流发生器，但是，正如两个EUROSHOCK计划所强调的，激波控制凸块是最有前途的激波控制系统之一（Stanewsky等人，1997年，Stanewsky等人，2002年）激波控制凸块通过操纵吸力面上的气流，有可能改善跨音速机翼的性能。它们通常采取小的局部变形形式，包括正激波标称位置上游的斜坡，产生近等熵压缩波并使正激波分叉，随后是尾部，使气流返回翼型表面（布鲁斯和Colliss 2014）。冲击控制凸起可以是2D或3D。在第一种情况下，凸块外形沿着翼展是恒定的;在第二种情况下，几个凸块沿着机翼布置。与（二维和三维）激波控制凸块有关的主要问题之一是，当激波相对于凸块顶部的位置改变时，设计时获得的有益的涂抹效应和滞止压力节省伴随着非设计阻力的增加。