A Study on Turbulent Heat Transfer Model in Aerodynamic Heating Fields with Dissociation

气动离解热场湍流传热模型研究

• 批准号: 11450377
• 负责人: ASO Shigeru
• 金额: $ 9.73万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B).
• 财政年份: 1999
• 资助国家: 日本
• 起止时间: 1999 至 2000
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-11450377/
• 关键词: Aerodynamic heating; High temperature effect; Shock wave; Spaceplane; Vibrational energy; Dissociation; Hypersonic flow; free-piston shock tunnel; 乱流熱伝達モデル; 衝撃波; フリーピストン衝撃波管; 衝撃風洞; 高温化学反応

For the design of spaceplanes and winged vehicles the accurate estimation of aerodynamic heating load is one of the most important problems. However, those estimations are quite difficult du to the lack of proper turbulent heat flux modeling. The purpose of the present study is to conduct the necessary experiments and computations, which are requested in order to build reliable turbulent heat flux modeling. In the present studies the following studies have been conducted.1) Free-piston high enthalpy shock tunnel has been built. The higher pressure of 250 - 500 bars has been realized at the end of the compression tube. Also characteristics of compression tube and the generation of very strong shock wave have been completed. The top Mach number of the generated shock wave is up to 34.5.(2) It is well known that free-piston high enthalpy shock tunnel has capability to generate high temperature and high pressure air and also the flow duration is quite short. The starting process of wind tu … More nnel is numerically simtulated and the condition for the starting of the nozzle is estimated.(3) The unsteady aerodynamic heating phenomena have been simulated and the effects of high temperature chemical reaction on unsteady aerodynamic heating phenomena have been revealed.(4) The interacting flow fields of shock wave and boundary layer have been simulated with chemically non-equilibrium conditions. The wall catalytic generates quite large difference in heat flux distributions at the wall. Also as the degree of non-equilibrium is increased, the calculated results show that the size of separation, heat flux distribution and pressure distribution can be hanged.(5) For the purpose of the construction of turbulent modeling hypersonic mixing flow fields and boat tail flow structure and high temperature nozzle flow of conventional nozzle have been simulated. Also turbulent modeling with high temperature effects has been considered.(6) Experimental studies on the reduction of aerodynamic heating loads at hypersonic flows have been conducted. Less

在空天飞机和有翼飞行器的设计中，气动热载荷的准确估算是一个非常重要的问题。然而，由于缺乏适当的湍流热通量模型，这些估计是相当困难的。本研究的目的是进行必要的实验和计算，这是为了建立可靠的湍流热通量模型的要求。本文主要开展了以下几方面的研究工作：1）建立了自由活塞高焓激波风洞。在压缩管的端部实现了250 - 500巴的较高压力。并对压缩管的特性和强激波的产生进行了研究.产生的激波最高马赫数可达34.5。(2)自由活塞式高焓激波风洞具有产生高温高压空气的能力，且气流持续时间较短。风力涡轮机的启动过程 ...更多信息 对喷管的起动条件进行了估算。(3)对非定常气动加热现象进行了数值模拟，揭示了高温化学反应对非定常气动加热现象的影响。(4)在化学非平衡条件下，模拟了激波与边界层干扰流场。壁面催化在壁面处产生了较大的热流分布差异。计算结果表明，随着非平衡度的增大，分离区的大小、热流密度分布和压力分布都将发生变化。(5)为了建立湍流模型，本文对常规喷管的高超声速混合流场、尾流结构和高温喷管流场进行了数值模拟。还考虑了具有高温效应的湍流模型。(6)在高超音速流动中，已经进行了减少气动热载荷的实验研究。少

项目成果

麻生 茂: "完全再使用型宇宙住還機開発におけるCFDへの期待"航空宇宙数値シミュレーション技術シンポジウム2000. (2000)

麻生茂：“在完全可重复使用航天器的开发中对 CFD 的期望”2000 年航空航天数值模拟技术研讨会。（2000 年）

A.Matsumoto and S.Aso: "Numerical Simulation of Shock-Wave/Boundary Layer Interaction with Chemical Nonequilibrium,"Proc.22nd.International Symposium on Shock Waves, Held at London, United Kingdom, at July 18-23,1999. (2000)

A.Matsumoto 和 S.Aso：“冲击波/边界层与化学非平衡相互作用的数值模拟”，Proc.22nd.International Symposium on Shock Waves，于 1999 年 7 月 18-23 日在英国伦敦举行。

K.Sugimoto, S.Aso, N.Tanatsugu and T.Murooka: "Numerical Analysis of Plug Nozzle Flow"Proc.of Aerospace CFD Technology Symposium 1999. 393-398 (1999)

K.Sugimoto、S.Aso、N.Tanatsugu 和 T.Murooka：“塞式喷嘴流动的数值分析”Proc.of Aerospace CFD Technology Symposium 1999. 393-398 (1999)

K.Sugimoto and S.Aso: "Numerical Simulations of Flow Field around Plug Nozzle for Various Flight Conditions"Proc.of 22nd International Symposium on Space Technology and Science, held at Morioka, Japan, on May 28-June 4, 2000. ists-2000-e-11. 919-923 (2000

K.Sugimoto 和 S.Aso：“各种飞行条件下塞式喷嘴周围流场的数值模拟”，2000 年 5 月 28 日至 6 月 4 日在日本盛冈举行的第 22 届空间技术与科学国际研讨会论文集。

S.Aso: "Computational Fluid Dynamics for the Development of Reusable Space Planes"Proc.of Aerospace CFD Technology Symposium 2000. (2000)

S.Aso：“用于开发可重复使用航天飞机的计算流体动力学”Proc.of Aerospace CFD Technology Symposium 2000。（2000）