強力なフラップを用いた双発STOL機の風胴試験(Ⅰ)

Material type: 文書・図像類

Author: 北村, 清美ほか

Publisher: 航空宇宙技術研究所

Publication date: 1974-09

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: In May 1965, the investigations of twin-propeller ultra short takeoff and landing (USTOL) airplane had been recommended by National Aeronautical Counc...

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: 強力なフラップを用いた双発STOL機の風胴試験(Ⅰ)
Author/Editor: 北村, 清美
高橋, 侔
鈴木, 友昭
KITAMURA, Kiyomi
TAKAHASHI, Hitoshi
SUZUKI, Tomoaki
Author Heading: 北村, 清美
高橋, 侔
鈴木, 友昭
KITAMURA, Kiyomi
TAKAHASHI, Hitoshi
SUZUKI, Tomoaki
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1974-09
Publication Date (W3CDTF): 1974-09
Alternative Title: Wind Tunnel Tests for Twin-propeller STOL Airplane having powerful Flaps(I)
Periodical title: 航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
No. or year of volume/issue: 262
Volume: 262
Pages: 39-
ISSN (Periodical Title): ISSN : 0452-2982
Text Language Code: jpn
Target Audience: 一般
Note (General): In May 1965, the investigations of twin-propeller ultra short takeoff and landing (USTOL) airplane had been recommended by National Aeronautical Council in Japan. In accordance with that recommendation, the wind tunnel investigations have been carried out with special emphasis on the aerodynamic characteristics of the STOL airplane at powered conditions. The model is equipped with powerful high lift devices, namely, double slats and multi- slotted flaps in full span. In order to attain such high lift force as possible, the full span flaps have been extended and deflected. For example, in the tests of landing configuration the inner flaps are deflected up to 90 degrees. In the results of these tests, the following aerodynamic characteristics of the model have been found. I. In the conditions without propellers, maximum lift coefficient CL exceeds 3.2, and the behavior of stall is much favourable. 2. In the powered condition with the thrust coefficient of TT=1.53, CL =6.9 is obtained. However, the non-linear characteristics of pitching moment have been observed. 3. There are some non-linear characteristics also in rolling moment coefficient C2 and yawing moment coefficient C. when the thrust coefficient TT is large. 4. The elevator and rudder effectivenesses are almost linear in spite of those non-linear characteristics. 5. The aileron has its effectiveness only the negative angles of deflection. The outer flaps (including the ailerons) seem to be arranged very tell to obtain high lift force. Hence, further deflection of the outer flaps would not help provide additional increase of lift force. In order to control the lateral dynamics, other roll control devices may be necessary. On the bases of these results, it is desirable to conduct extensive investigations on such non-linear aerodynamic characteristics in the future.
資料番号: NALTM0262000
レポート番号: NAL TM-262
Access Restrictions: 限定公開
Periodical Title (NCID): AN00314334
https://ci.nii.ac.jp/ncid/AN00314334
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