菱形結合翼機4形態の低速風洞実験

Material type: 文書・図像類

Author: 岩崎, 昭人ほか

Publisher: 航空宇宙技術研究所

Publication date: 1992-07

Material Format: Digital

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Note (General)：: 主翼に後退角と上反角をつけ、水平尾翼に前進角と下反角をつけて、両者を結合した菱型結合翼機は新しいタイプの航空機として風洞試験や数値解析が行われている。菱型結合翼機の基本的な空力特性を得ることを目的として、水平尾翼の翼幅および主翼との結合位置を変化させた4形態の菱型結合翼機について低速風洞試験を行った...

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Material Type: 文書・図像類
Title: 菱形結合翼機4形態の低速風洞実験
Author/Editor: 岩崎, 昭人
藤田, 敏美
藤枝, 郭俊
滝澤, 直人
Iwasaki, Akihito
Fujita, Toshimi
Fujieda, Hirotoshi
Takizawa, Naoto
Author Heading: 岩崎, 昭人
藤田, 敏美
藤枝, 郭俊
滝澤, 直人
Iwasaki, Akihito
Fujita, Toshimi
Fujieda, Hirotoshi
Takizawa, Naoto
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1992-07
Publication Date (W3CDTF): 1992-07
Alternative Title: Low-speed wind tunnel tests on four types of joined-wing aircraft models
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory
No. or year of volume/issue: 1167
Volume: 1167
Pages: 1-22
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Subject Heading: 結合翼
先進航空機形態
省エネルギー型航空機
新世代航空機
低速風洞試験
空力特性
誘導抵抗減少
揚抗比
主翼尾翼干渉
水平尾翼形状効果
上反角効果
前縁デバイス
菱形平面形翼
系統試験
後退翼
joined wing
advanced aircraft configuration
energy efficient airplane
new generation airplane
low speed wind tunnel test
aerodynamic characteristic
induced drag reduction
lift to drag ratio
wing tail interference
horizontal tail configuration effect
dihedral angle effect
leading edge device
rhombic planform wing
parameter study
sweptback wing
Target Audience: 一般
Note (General): 主翼に後退角と上反角をつけ、水平尾翼に前進角と下反角をつけて、両者を結合した菱型結合翼機は新しいタイプの航空機として風洞試験や数値解析が行われている。菱型結合翼機の基本的な空力特性を得ることを目的として、水平尾翼の翼幅および主翼との結合位置を変化させた4形態の菱型結合翼機について低速風洞試験を行った。その結果、結合翼機では主翼の吹下ろしと剥離が全機空力特性に大きな影響を与えること、ならびに、主翼と水平尾翼の翼端を重ねた形態では揚力低下や早期失速を招くことがわかった。
Low-speed wind tunnel tests were conducted on four types of joined-wing aircraft models. Various ratios of horizontal tail to wing span were employed (40 percent, 60 percent and 100 percent.), and the leading-edge at the tip of horizontal tail was joined to the trailing-edge of the wing for three configurations. In addition, in one configuration the tips of the horizontal tail and the wing were overlapped using the 100 percent ratio. The horizontal tail has minus 22 deg dihedral and minus 25 deg sweep angles (25 percent chord line). And the main wing has respectively corresponding angles of 10 deg and 40 deg. The results indicated that the area and location of horizontal tail significantly effect the aerodynamic characteristics of the joined-wing aircraft.
資料番号: AA0004184000
レポート番号: NAL TR-1167
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