Transdisciplinary Research for Silent Supersonic Aircraft by Integrating Computation and Experiment

计算与实验相结合的超音速静音飞机跨学科研究

• 批准号: 15206091
• 负责人: OBAYASHI Shigeru
• 金额: $ 31.62万
• 依托单位: TOHOKU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 2003
• 资助国家: 日本
• 起止时间: 2003 至 2006
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-15206091/
• 关键词: Super Sonic Flow; Sonic Boom; Shock Wave; Aircraft Design; Computational Fluid Dynamics; Optimization; Pressure Sensitive Paint; Parallel Computation

One of the fundamental problems preventing commercial transport aircraft from supersonic flight is the generation of strong sonic booms. The strength of the shock waves generated by an aircraft flying at supersonic speed is a direct function of both the aircraft's weight and its occupying volume; it has been very difficult to sufficiently reduce the shock waves generated by the heavier and larger conventional supersonic transport (SST) configuration to meet acceptable at-ground sonic-boom levels.Our team first re-analyzed the classic Busemann biplane configurations to understand its basic wave cancellation concept using modern Computational Fluid Dynamics (CFD) tools. We then designed a two-dimensional (2-D) supersonic biplane that not only shows the desired aerodynamic characteristics at its design condition, but also outperforms a zero-thickness flat-plate airfoil. (Zero-thickness plat-plate airfoils are known as the most efficient monoplane airfoil at supersonic speeds.) Also we studied biplane performance not only at their design Mach numbers but also at off-design conditions. We extended the analysis to 3-D wing configurations as well.In parallel to the computational studies, we carried out series of experiments. The first experiment conducted here was the sonic boom experiment using gas gun. The N-wave was captured successfully. The second experiment was the 2 D wind tunnel test using Indraft Wind Tunnel Facility newly constructed in this research. In addition, conventional wind tunnel tests were conducted using existing wind tunnels. These experiments revealed important off-design flow features to be further studies by using CFD.The main research result is the development of the supersonic biplane theory. Biplane configuration allows canceling shock waves created by supersonic objects. It can be unconventional and innovative concept for future supersonic transport.

阻止商用运输机进行超音速飞行的基本问题之一是产生强烈的音爆。以超音速飞行的飞机所产生的冲击波的强度是飞机重量和所占体积的直接函数;由于常规超音速运输机（SST）的重量较大，所以要充分地减小它所产生的激波，使之达到地面上可接受的音爆水平，是非常困难的。使用现代计算流体动力学（CFD）工具分析了经典的Busemann双翼构型，以了解其基本的消波概念。然后，我们设计了一个二维（2-D）的超音速双翼，不仅显示出所需的气动特性在其设计条件下，但也优于零厚度平板翼型。（零厚度平板翼型被认为是超音速时最有效的单翼翼型。此外，我们研究了双翼机的性能，不仅在他们的设计马赫数，而且在非设计条件。我们还将分析扩展到三维机翼构型，在进行计算研究的同时，我们还进行了一系列的实验。这里进行的第一个实验是使用气炮的音爆实验。成功捕获N波。第二个实验是使用本研究中新建立的内吸风洞设备进行的二维风洞实验。此外，还利用现有风洞进行了常规风洞试验。这些实验揭示了一些重要的非设计流场特征，有待于用CFD方法进一步研究，主要研究成果是发展了超声速双翼机理论。双平面配置允许消除超音速物体产生的冲击波。它可以是未来超音速运输的非传统和创新概念。

项目成果

Drag Reduction of a Near-Sonic Airplane by Using Computational Fluid Dynamics

• DOI: 10.2514/1.15059
• 发表时间: 2005-09
• 期刊: AIAA Journal
• 影响因子: 2.5
• 作者: Wataru Yamazaki;K. Matsushima;K. Nakahashi

レーザーピーニングで誘起される水中圧力波に対する金属板厚の影響

金属板厚度对激光喷丸水下压力波的影响

• 发表时间: 2004
• 期刊: Science and Technology of Energetic Materials 65・5
• 作者: 渡辺圭子;佐野雄二;向井成彦;鳥飼宏之;佐宗章弘
• 通讯作者: 佐宗章弘

Lae Sung Kim: "Navier-Stokes Computations of Multi-Element Airfoils"Computational Fluid Dynamics Journal. 12・1. 107-114 (2003)

Lae Sung Kim：“多元素翼型的纳维-斯托克斯计算”计算流体动力学杂志 12・1（2003）。

Ryoji Takaki: "The Development of the UPACS CFD Environment"Lecture Notes in Computer Science. 2858. 307-319 (2003)

Ryoji Takaki：“UPACS CFD 环境的开发”计算机科学讲义。

運動量理論を用いた超音速流れでの揚・抗力値予測

使用动量理论预测超音速流中的升力和阻力值

• 发表时间: 2006
• 期刊: 日本航空宇宙学会論文集 54
• 作者: 長和剛平;伊藤秀昭;菅芳樹;羽藤英二;Ko Higashitani;山崎 渉
• 通讯作者: 山崎 渉