Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing
Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing
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有限超音速双翼机翼启动/非启动特性的风洞测试
DOI：
10.1155/2013/231434
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发表时间：
2013
影响因子：
1.4
通讯作者：
and Shigeru Obayashi
中科院分区：
文献类型：
--
作者：
Hiroshi Yamashita;Naoshi Kuratani;Masahito Yonezawa;Toshihiro Ogawa;Hiroki Nagai;Keisuke Asai;and Shigeru Obayashi
本研究描述了有限长矩形超音速双翼机机翼的起动/非起动特性。在风洞中对展弦比为0.75（模型A）和2.5（模型B）的两个机翼模型进行了试验。模型由Busemann双翼剖面组成。试验是在马赫数为0.3 ≤M∞≤ 2.3的范围内，利用超音速和跨音速风洞进行的，迎角分别为0°、2°和4°。利用纹影系统观察了模型周围的流动特性。实验结果表明，由于三维效应，这些模型具有与Busemann双平面（二维）不同的启动/非启动特性。A型和B型在比Busemann双翼机更低的马赫数下起动。这些特性也随展弦比而变化：由于展弦比较低，模型A（1.3 <M∞< 1.5）的起始马赫数低于模型B（1.6 <M∞< 1.8）。模型B在M ∞= 1.7时处于启动/非启动特性的双解域，模型B在M ∞= 1.7时处于启动或非启动状态。一旦确定了状态，任何一种状态都是稳定的。
This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing. Two wing models were tested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B). The models were composed of a Busemann biplane section. The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of 0.3 ≤M∞≤ 2.3 with angles of attack of 0°, 2°, and 4°. The Schlieren system was used to observe the flow characteristics around the models. The experimental results showed that these models had start/unstart characteristics that differed from those of the Busemann biplane (two dimensional) owing to three‐dimensional effects. Models A and B started at lower Mach numbers than the Busemann biplane. The characteristics also varied with aspect ratio: model A (1.3 <M∞< 1.5) started at a lower Mach number than model B (1.6 <M∞< 1.8) owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart characteristics atM∞= 1.7, and model B was in either the start or unstart state atM∞= 1.7. Once the state was determined, either state was stable.
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无吊杆锥形超音速双翼飞机启动过程中小翼气动特性及影响
影响因子：
1.1
作者：
Hiroshi YAMASHITA;Takashi FUJISONO;Atsushi TOYODA;Hiroki NAGAI;Keisuke ASAI;Shinkyu JEONG;Shigeru OBAYASHI
通讯作者：
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DOI：
--
发表时间：
2006
期刊：
Proceedings of 25th International Congress of the Aerospace Sciences ICAS2006-3.7.2
影响因子：
--
作者：
T. Kugita;et. al.;D. Maruyama;D. Maruyama;K. Matsushima;Wataru YAMAZAKI;D. Maruyama;R. Nakayama;D. Maruyama;K. Matsushima;Wataru YAMAZAKI;D. Maruyama;R. Nakayama;Wataru YAMAZAKI;Takumi Matsuzawa;D. Maruyama;K. Matsushima;D. Maruyama;R. Nakayama;Wataru YAMAZAKI;中山亮;楠瀬 一洋;Daigo Maruyama;R. Nakayama;Kazuhiro Kusunose;Daigo Maruyama;Kazuhiro Kusunose;D. Maruyama;中山 亮;楠瀬 一洋;Daigo Maruyama;Kazuhiro Kusunose;松澤 拓未;Kisa Matsushima
通讯作者：
Kisa Matsushima
影响因子：
2.2
作者：
D. Maruyama;K. Kusunose;K. Matsushima
通讯作者：
D. Maruyama;K. Kusunose;K. Matsushima
DOI：
10.2514/3.6478
发表时间：
1971
期刊：
影响因子：
--
作者：
A. George;R. Seebass
通讯作者：
R. Seebass
影响因子：
27.7
作者：
J. Alonso;M. Colonno
通讯作者：
M. Colonno