超音速飛しょう体頭部形状まわりの空力加熱解析

Material type: 文書・図像類

Author: 片山, 雅之ほか

Publisher: 航空宇宙技術研究所

Publication date: 1991-12

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: Aerodynamic heating analyses have been performed for axisymmetric bodies in the supersonic flow. both experiments using a shock tunnel and the computa...

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 Institutional Repositories DataBase(IRDB)(Institutional Repository) is linked at the site of Institutional Repositories DataBase(IRDB)(Institutional Repository).
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: 超音速飛しょう体頭部形状まわりの空力加熱解析
Author/Editor: 片山, 雅之
黒崎, 隆二郎
中村, 淑子
麻生, 茂
熊坂, 和広
Katayama, Masayuki
Kurosaki, Ryujiro
Nakamura, Yoshiko
Aso, Shigeru
Kumasaka, Kazuhiro
Author Heading: 片山, 雅之
黒崎, 隆二郎
中村, 淑子
麻生, 茂
熊坂, 和広
Katayama, Masayuki
Kurosaki, Ryujiro
Nakamura, Yoshiko
Aso, Shigeru
Kumasaka, Kazuhiro
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1991-12
Publication Date (W3CDTF): 1991-12
Alternative Title: Aerodynamic Heating Analysis for Axisymmetric Bodies in Supersonic Flow
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16
No. or year of volume/issue: 16
Volume: 16
Pages: 245-250
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): Aerodynamic heating analyses have been performed for axisymmetric bodies in the supersonic flow. both experiments using a shock tunnel and the computations corresponding to the experiments are conducted. Heat flux to the bodies such as a hemisphere-cylinder and an ogive-cylinder are measured. Flow conditions are (1) Mach number M infinity = 4.25 (2) Reynolds numbers Re infinity = 2 - 3x105, based on body radius (3) Stagnation temperatures T0 = 500 - 600K (4) Angle of attack alpha = 0 degrees Results of the experiments and the computations are summarized as follows. Heat flux to the hemisphere surface has the maximum value at the stagnation point and decreases smoothly downstream. Also the heat flux to the ogive surface is quite large in the vicinity of the tip and decreases gradually downstream in the case of fully laminar or fully turbulent flow. In the case of the flow including the transition, increase of heat flux caused by the transition of the boundary layer is observed. LU-ADI difference scheme for compressible Navier-Stokes Code has been used for the computations corresponding to the experiments. Computational results show good correlation to the experimental data obtained by the shock tunnel.
資料番号: NALSP0016039
レポート番号: NAL SP-16
Access Restrictions: 限定公開
Periodical Title (NCID): AN10097345
https://ci.nii.ac.jp/ncid/AN10097345
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