遷音速全機形状まわりのパネル法計算と風洞試験の比較

Material type: 文書・図像類

Author: 海田, 武司ほか

Publisher: 航空宇宙技術研究所

Publication date: 1988-12

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: The rapid progress of the computational aerodynamics enables us to analyze airflow with viscous calculation instead of with invisid one. In two-dimens...

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: 遷音速全機形状まわりのパネル法計算と風洞試験の比較
Author/Editor: 海田, 武司
宮川, 淳一
柳沢, 三憲
天野, 完一
Kaiden, Takeshi
Miyakawa, Jun-ichi
Yanagisawa, Mitsunori
Amano, Kan-ichi
Author Heading: 海田, 武司
宮川, 淳一
柳沢, 三憲
天野, 完一
Kaiden, Takeshi
Miyakawa, Jun-ichi
Yanagisawa, Mitsunori
Amano, Kan-ichi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1988-12
Publication Date (W3CDTF): 1988-12
Alternative Title: Comparison with Computation Using Panel Method and Wind Tunnel Test Around Transonic Complete Aircraft
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-9
No. or year of volume/issue: 9
Volume: 9
Pages: 141-150
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): The rapid progress of the computational aerodynamics enables us to analyze airflow with viscous calculation instead of with invisid one. In two-dimensional application, we have already validated its effectiveness in comparison with wind tunnel testing and put it into practical stage. In three-dimensional application, the wing-body configulation has been also done. This paper presents a validative discussion of the panel method toward the analysis about the complete aircraft, including the calculation of the sting interference, which is indispensable to wind tunnel testing. The results indicate that the panel method is valid in the subsonic region and that the sting makes up wash flow.
資料番号: NALSP0009021
レポート番号: NAL SP-9
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43312&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43312&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