航空機の環境適合性・安全性向上のための直交格子法に基づく非定常流の数値解析

基于正交网格法的非定常流数值分析提高飞机环境兼容性和安全性

• 批准号: 16J07740
• 负责人: 玉置 義治
• 金额: $ 0.58万
• 依托单位: The University of Tokyo
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for JSPS Fellows
• 财政年份: 2016
• 资助国家: 日本
• 起止时间: 2016-04-22 至 2018-03-31
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-16J07740/
• 关键词: 直交格子; 乱流境界層; 埋め込み境界法; 非定常流; 乱流解析

本年度はまず，昨年度開発した直交格子における乱流解析用壁面境界条件を検証するとともに，そのベースである直交格子ベース流体ソルバの機能のさらなる拡充を行った．その1点目として，複雑な形状周りでの解析を可能とするために，境界条件の設定方法等の開発・検討を行った．またその結果を用い，高揚力装置展開状態での航空機全機周りの乱流解析がロバスト行えることを実証した．2点目として，開発した壁面境界条件を用いることのできる格子の条件についての調査を行った．2次元の平板上の乱流境界層の解析では，格子幅を境界層厚みの1/50以下とすれば表面摩擦係数が5%以内で再現できること，境界条件の決定に使用するイメージポイントは，壁面から格子幅の3倍以上離れた場所に設置するのが望ましいことを確認した．この結果に基づき，航空機全機周り流れ場の解析に必要な格子等の見積もり・実証を行った．以上の手法を用いて，非定常流れ場の解析を行った．非定常計算で従来広く用いられている乱流モデルであるDelayed-Detached Eddy Simulationを直交格子で用いた場合，乱流境界層が正しく再現できないことを確認した．そこで，乱流モデルの改良を行い，乱流境界層の計算における格子依存性を低減した．この乱流モデルを用いて遷音速・高迎角における翼の数値計算を行ったところ，実験で観察されるような衝撃波背後での流れの剥離・付着の繰り返しと，それに伴う衝撃波の振動が再現された．併せて，高揚力装置30P30N周りの非定常流れ場を数値計算し，翼前縁のスラットから放出される空力音の予測を行った．以上のように，非定常乱流解析を行う上で必要な諸要素の開発・検証および，それらを用いて航空機に関連した非定常流れ場を計算，物理の考察を行った．よって，所期の目的である「航空機の環境適合性・安全性向上」に資する知見を得ることが出来たと考える．

This year, the orthogonal lattice system was developed last year. The wall boundary conditions for turbulence analysis were tested and verified. The orthogonal lattice system was used for fluid analysis. The first point is that the analysis of the complex shape cycle is possible, and the development of the setting method of the boundary condition is discussed. The results show that the turbulence analysis of the whole aircraft circumference in the deployed state of the high-lift device is carried out in the following ways: 1. the turbulence analysis of the whole aircraft circumference in the deployed state of the high-lift device is carried out in the following ways: 2. the turbulence analysis of the whole aircraft circumference in the deployed state of the high-lift device is carried out in the following ways: 1. the turbulence analysis of the whole aircraft circumference in the deployed state of the high-lift device is carried out in the following ways: 2. the turbulence analysis of the whole aircraft circumference in the deployed state of the high-lift device is carried out in the following ways: 1. the turbulence analysis of the turbulence boundary layer on the flat plate in the second dimension is carried out in the following ways: 2. the turbulence analysis of the boundary layer on the flat plate in the second dimension is carried out in the following ways: 2. the turbulence analysis of the boundary layer on the flat plate in the second dimension is carried out in the second dimension. The thickness of the lattice layer is less than 1/50, and the surface friction coefficient is less than 5%. The boundary condition is determined by using the method of determining the thickness of the lattice layer. The wall surface is more than 3 times the thickness of the lattice layer. The results of this research are based on the analysis of the flow field in the whole aircraft. The above methods are applied to the analysis of unsteady flow fields. Unsteady calculation is a case where the turbulent boundary layer is positive and the turbulent boundary layer is positive. The improvement of turbulence boundary layer calculation reduces the lattice dependence. The turbulent flow is caused by the velocity of sound and the number of wings at high angles of attack. The flow behind the shock wave is caused by the separation of the shock wave and the vibration of the shock wave. In addition, the unsteady flow field of the high lift device 30P30N is numerically calculated, and the air force sound is predicted. The analysis of unsteady turbulence is necessary for the development and verification of various factors, and the calculation of unsteady flow fields in aircraft is necessary for the investigation of physics. The objective of the project is to provide information on the environmental suitability and safety of aircraft.

项目成果

Turbulent Flow Simulations of the NASA Common Research Model using the Immersed Boundary Method with a Wall Function

• DOI: 10.2514/6.2017-4235
• 发表时间: 2017-06
• 作者: Yoshiharu Tamaki;T. Imamura

埋め込み境界法における力計算精度と質量保存則の関連性の調査

嵌入式边界法中力计算精度与质量守恒定律关系的研究

• 发表时间: 2016
• 作者: Tamaki;Y.;Imamura;T.;玉置義治，今村太郎;玉置義治，今村太郎;玉置義治，今村太郎;玉置義治，今村太郎
• 通讯作者: 玉置義治，今村太郎

Inviscid and RANS Simulation of the NASA-CRM Using the Cartesian Flow Solver UTCart

使用笛卡尔流求解器对 NASA-CRM 进行无粘性和 RANS 仿真 UTCart

• DOI: 10.2322/astj.jsass-d-17-00024
• 发表时间: 2018
• 期刊: AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
• 作者: Kunishima;T.;R. Iwamoto;M. Iida and K. Tachihara;玉置義治，原田基至，今村太郎
• 通讯作者: 玉置義治，原田基至，今村太郎

Simulation of 30P30N on Cartsian Grids with Immersed Boundary Method

笛卡尔网格上30P30N的浸入边界法仿真

• 发表时间: 2016
• 作者: Tamaki;Y.;Harada;M. and Imamura;T.
• 通讯作者: T.

A Simple and Robust Cut Cell Method for High-Reynolds-Number Flow Simulation on Cartesian Grids

笛卡尔网格上高雷诺数流动模拟的简单而稳健的切割单元方法

• 发表时间: 2017
• 期刊: AIAA Journal
• 影响因子: 2.5
• 作者: Harada;M.;Tamaki;Y. and Imamura;T.
• 通讯作者: T.