複雑な形状の航空機まわりの流れの数値シミュレーション

Material type: 文書・図像類

Author: 橘, 正和ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-11

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: A numerical aerodynamic simulation system applicable to various complex geometries was developed. We use an O-O type of grid in order to concentrate g...

Search by Bookstore

Holdings of Libraries in Japan

This page shows libraries in Japan other than the National Diet Library that hold the material.

List of Cooperating Institutions and Databases

Please contact your local library for information on how to use materials or whether it is possible to request materials from the holding libraries.

other

JAXA Repository
Digital
You can check the holdings of institutions and databases with which 学術機関リポジトリデータベース（IRDB）（機関リポジトリ） is linked at the site of 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）.
JAXA Repository

Search by Bookstore

Bibliographic Record

You can check the details of this material, its authority (keywords that refer to materials on the same subject, author's name, etc.), etc.

Digital

Material Type: 文書・図像類
Title: 複雑な形状の航空機まわりの流れの数値シミュレーション
Author/Editor: 橘, 正和
高梨, 進
Tachibana, Masakazu
Takanashi, Susumu
Author Heading: 橘, 正和
高梨, 進
Tachibana, Masakazu
Takanashi, Susumu
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-11
Publication Date (W3CDTF): 1989-11
Alternative Title: Numerical Simulation of Flow Fields around a Airplane of Complex Geometries
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-10
No. or year of volume/issue: 10
Volume: 10
Pages: 195-200
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): A numerical aerodynamic simulation system applicable to various complex geometries was developed. We use an O-O type of grid in order to concentrate grid points in wall boundary layers effectively and to implement wall and outer boundary conditions easily. In addition, on the body surface, the grid is devided into several blocks which have common points at each interface. By doing so, a finite volume algorithm can be applied easily and the Navier-Stokes code using this grid became adaptable to various kinds of airplanes. As a first example, we tried to compute the flowfield around a practical aircraft configuration, and also compared the solution with the wind tunnel test data.
資料番号: NALSP0010033
レポート番号: NAL SP-10
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43362&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43362&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ