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

Flow separation characteristics on diamond wing for various leading-edge roughness

各种前沿粗糙度的金刚石翼上的流动分离特性

基本信息

批准号：
278432771
负责人：
Professor Dr.-Ing. Christian Breitsamter
金额：
--
依托单位：
Lehrstuhl für Aerodynamik und Strömungsmechanik
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2015
资助国家：
德国
起止时间：
2014-12-31 至 2018-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/278432771?language=en
关键词：
Flow separation characteristics diamond wing

项目摘要

At wing configurations featuring moderate leading-edge sweep and blunt leading-edges, the flow separates in the leading-edge area at moderate angles of attack while the subsequent vortex formation extends only over a portion of the leading-edge. Towards the apex there is attached flow. The flow separation topology depends in particular on the Reynolds number and the roughness of the leading edge, i.e. whether the primary separation is associated with a laminar, transition or turbulent type boundary layer or a turbulent separation linked to a rough wall. In addition, due to the moderate leading-edge sweep, the partially developed vortex already burst after a relatively short development length. Apart from the actual leading-edge vortex (main vortex) there may be a further vortex-like flow separation along the inner wing part. In contrast to the cases with strong, fully developed leading- edge vortices, a precise analysis associated with partially developed leading-edge vortices and their main parameters justify detailed further research. Consequently, the objective of this project is to investigate the evolution and development of partly developed leading-edge vortices and corresponding flow separation as a function of the boundary layer state and leading-edge roughness using a generic diamond wing configuration. Complementary wind tunnel tests and numerical simulations have to be performed. Thus, features of the vortex structures and criteria for the transient characteristics are to be derived. Another objective is to evaluate the use of Navier-Stokes methods to this problem in terms of the quality of results, employing scale adaptive turbulence modeling and scale resolution techniques.

在前缘掠度适中和前缘钝的机翼构型中，气流在前缘区域以中等迎角分离，而随后形成的涡只延伸到前缘的一部分。向顶点方向有附流。流动分离的拓扑结构主要取决于雷诺数和前缘的粗糙度，即初级分离是与层流、过渡或湍流型边界层相关联，还是与粗糙壁面相关联的湍流分离。此外，由于前缘掠度适中，部分发展的涡在较短的发展长度后就已经破裂。除了实际的前缘涡（主涡）外，沿内翼部分可能存在进一步的涡状流动分离。与强而充分发展的前缘涡相比，对部分发展的前缘涡及其主要参数的精确分析证明了进一步的详细研究是正确的。因此，本项目的目的是研究部分发展的前缘涡的演变和发展，以及相应的流动分离作为边界层状态和前缘粗糙度的函数，使用通用的钻石翼结构。必须进行互补的风洞试验和数值模拟。因此，涡结构的特征和瞬态特性的判据将被导出。另一个目标是评估在结果质量方面使用Navier-Stokes方法来解决这个问题，采用尺度自适应湍流建模和尺度分辨率技术。