| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
強力なフラップを用いた双発STOL機の風胴試験(Ⅰ) |
| 言語 |
|
|
言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
資源タイプ |
technical report |
| その他のタイトル（英） |
|
|
その他のタイトル |
Wind Tunnel Tests for Twin-propeller STOL Airplane having powerful Flaps(I) |
| 著者 |
北村, 清美
高橋, 侔
鈴木, 友昭
KITAMURA, Kiyomi
TAKAHASHI, Hitoshi
SUZUKI, Tomoaki
|
| 著者所属 |
|
|
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
|
|
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
|
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|
特許庁 |
| 出版者 |
|
|
出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
|
|
出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所資料
en : Technical Memorandum of National Aerospace Laboratory
巻 262,
p. 39,
発行日 1974-09
|
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
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. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0452-2982 |
| 書誌レコードID |
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|
収録物識別子タイプ |
NCID |
|
収録物識別子 |
AN00314334 |
| 資料番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTM0262000 |
| レポート番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TM-262 |
naltm00262.pdf (1.3 MB)
