Theoretical study on the aerodynamic effect of mutual interaction in multi-body problems

多体问题中相互作用气动效应的理论研究

基本信息

批准号：
17560695
负责人：
MATSUSHIMA Kisa
金额：
$ 2.35万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
2005
资助国家：
日本
起止时间：
2005 至 2007
项目状态：
已结题

项目摘要

(1) A high performance aerodynamic device which utilizes supersonic multi element aerodynamics has been proposed. Biplane wings have been researched using computational fluid dynamics (CFD). Those wings realize almost drag-less performance by utilizing favorable interaction between pressure waves of two wing elements. Through the research in 2005 and 2006 years, one of the best biplane airfoil was designed. It has sufficient lift for the cruise with the speed of Mach 1.7 and the lift-drag ratio (l/d) is 21. This is the first time in the world to show that a lifted biplane can have such a high l/d performance. In 2007, biplane wings has been investigated by extending the designed airfoil to a three dimensional device. It has been also confirmed that an airfoil/wing design system, which has been developed in this project, works efficiently and accurately for the both of 2D and 3D design problems.(2) Detailed CFD analysis about multi body problems in a subsonic flow-field has been conducted A flow-field around aircraft has been simulated at the Mach number of 0.2. The configuration consists of a fuselage, an engine nacelle and a wing which has a slat and a flap in extended condition. Basic flow equations are Reynolds averaged Navier-Stokes ones. There occur many interactions between a slat and a main-wing, a wing and a nacelle etc. Therefore, the flow phenomena must be complicated. we intended to obtain useful data to model aerodynamic interaction. The computations have been conducted using grid distribution as high density as possible. At the present, qualitatively we have obtained reliable data. However, for the detailed analysis, the current resolution level is not sufficient. It is needed to devise advanced numerical techniques to analyze separated flow-fields, vortices and free sheer layers.

(1)提出了一种利用超音速多元件空气动力学的高性能气动装置。双翼飞机机翼已通过计算流体动力学 (CFD) 进行研究。这些机翼通过利用两个机翼元件的压力波之间的有利相互作用实现了几乎无阻力的性能。通过2005年和2006年的研究，设计出了最好的双翼机翼型之一。它具有足够的升力用于巡航，速度为1.7马赫，升阻比（l/d）为21。这是世界上首次证明升力双翼飞机可以具有如此高的l/d性能。 2007年，通过将设计的翼型扩展到三维装置，对双翼机翼进行了研究。还证实，本项目开发的翼型/机翼设计系统能够高效、准确地解决 2D 和 3D 设计问题。(2) 亚音速流中多体问题的详细 CFD 分析-已对飞机周围的流场进行了模拟，马赫数为 0.2。该结构由机身、发动机短舱和机翼组成，机翼具有处于展开状态的缝翼和襟翼。基本流动方程是雷诺平均纳维-斯托克斯方程。缝翼与主翼、机翼与机舱等之间会发生多种相互作用，因此流动现象必然很复杂。我们的目的是获得有用的数据来模拟空气动力相互作用。计算是使用尽可能高密度的网格分布进行的。目前，我们已经定性地获得了可靠的数据。然而，对于详细分析，当前的分辨率水平还不够。需要设计先进的数值技术来分析分离流场、涡流和自由剪切层。