風洞試験における二、三の問題について(遷音速での試験精度を阻害する要因)

Material type: 文書・図像類

Author: 河本, 巖ほか

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)：: Two problems concerning the data accuracy in transonic wind tunnel testing are described. One is the side wall boundary layer interference problem in ...

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: 風洞試験における二、三の問題について(遷音速での試験精度を阻害する要因)
Author/Editor: 河本, 巖
Kawamoto, Iwao
Author Heading: 河本, 巖
Kawamoto, Iwao
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1991-12
Publication Date (W3CDTF): 1991-12
Alternative Title: Two Problems Reducing the Data Accuracy in Transonic Wind tunnel Testing
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: 305-312
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): Two problems concerning the data accuracy in transonic wind tunnel testing are described. One is the side wall boundary layer interference problem in the airfoil testing. In the transonic airfoil testing, it is believed that the side wall B.L. suction brings the improvement of the two-dimensionality of the airfoil surface flow. But it is not so simple. In NAL 2D high Reynolds number transonic wind tunnel, the measurements of side wall boundary layer thickness, Mach number distribution along center line and pressure distribution on NACA0012 airfoil were conducted with and without side wall boundary layer suction through a pair of rigimeshes. Following conclusions are derived in the present experimental studies. The B.L. suction system was not useful for the improvement of the airfoil surface flow, then theoretical side wall boundary layer correction such as Barnwell and Murthy methods should be employed to the data used solid side walls at the present time. Another problem presented here is transition Reynolds number of the experimental model. Using the AEDC standard cone, transition Reynolds numbers in several large transonic wind tunnels including NAL2m x 2mTWT are compared with flight data emphasizing the effects of back ground noise Cprms. Present comparative study shows that at low Mach number region Cprms does not promote the transition point forward and at high Mach number region the transition point is moved forward with large Cprms.
資料番号: NALSP0016048
レポート番号: NAL SP-16
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43544&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43544&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