Standard model testing in the European High Enthalpy Facility F4 andextrapolation to flight

Lourme, D.; Muylaert, J.; Papirnyk, O.; Devezeaux, D.; Walpot, L.; Häuser, J.; Sagnier, Ph.; Chatillon,

doi:10.2514/6.1992-3905

Cited by 21 publications

(10 citation statements)

References 2 publications

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“…The numerical method is validated by flight data of the ELECTRE vehicle [12,21] and test measurement data in the arc-heated wind tunnel [22]. The ELECTRE vehicle is a sphero-conical configuration with an overall length of 2 m, cone half-angle of 4.6 degrees, and nose radius of 0.175 m. One trajectory point is chosen with the free stream condition of altitude 53.3 km and Mach number 13 [21]. The fixed wall temperature of 343 K is assumed for the fully catalytic and noncatalytic wall boundary conditions.…”

Section: Methods Validationmentioning

confidence: 99%

“…The reliability of the numerical method is validated for flight conditions, because of an error of 10% to 15% in the computation originating from the uncertainties in free stream conditions, thermocouple signal, etc. [21]. The blunt test model is chosen to validate the numerical method, with a nose radius of 0.15 m, a shoulder radius of 0.005 m, an overall radius of 0.12 m, and a length of 0.08 m; its cross-section is shown in Figure 3.…”

Section: Methods Validationmentioning

confidence: 99%

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Study on the Simulation Method of the Ground Test in the Arc-Heated Wind Tunnel

Luo

Yang

Liang

et al. 2020

International Journal of Aerospace Engineering

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To analyze the effectiveness of the thermal assessment test, the simulation method of the ground test in the arc-heated wind tunnel is studied. Based on the solution of the thermochemical nonequilibrium Navier-Stokes equations, the flowfield around the spherical cylinder is simulated in the flight and ground test conditions, and the difference in the high enthalpy flowfield between the flight and ground test conditions is investigated. The flight parameters and ground test conditions are selected according to the criterion that the total enthalpy and the stagnation point heat flux of the fully catalytic cold wall (calibrated heat flux) are similar. The flowfield for different temperature boundaries and different catalytic walls is solved under the same free stream conditions, and the stagnation point heat flux and oxygen atom mass fraction are compared and analyzed. It is found that the heat flux on the fully catalytic wall for the radiation balance temperature boundary in the ground test is lower than that in the corresponding flight condition, but the difference is not obvious on the noncatalytic wall. In addition, the oxygen atom mass fraction after the shock wave in the ground test is higher than that in the corresponding flight condition. To make the stagnation point heat flux and oxygen atom mass fraction after the shock wave similar to those of the flight, the simulation method of the arc-heated wind tunnel test needs to be adjusted.

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Section: Methods Validationmentioning

confidence: 99%

Section: Methods Validationmentioning

confidence: 99%

Study on the Simulation Method of the Ground Test in the Arc-Heated Wind Tunnel

Luo

Yang

Liang

et al. 2020

International Journal of Aerospace Engineering

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show abstract

“…Figure Effect of high temperature real gas aerodynamic characteristics [120] , (a) Coefficient of axial force, (b) Coefficient of normal force, (c) Coefficient of pitch moment 高温真实气体效应的风洞试验研究需要依靠高焓试验装置，是高温气体效应研究的主要手段。目前高焓风洞主要面临三个问题 [1,121] ：一是高超声速飞行条件下的气流总温难以复现；二是化学反应的进程不随模型缩比发生变化，而纯净的空气来流和足够大的试验段尺寸在高焓风洞实现原理和工程实现上难以达到；三是气流速度难以复现。同时高焓流动实验中的高温、高速气流对实验装置的损坏较大，非接触式测量在测量精度等方面有待提高，这些因素都限制了高温气体效应风洞试验研究。国内外建成了许多高焓风洞，如中国科学院力学所的 JF12 [122] 爆轰驱动激波风洞、美国加州理工大学的 T5 自由活塞驱动激波风洞 [123] 和美国 LENS 系列加热轻气体驱动激波风洞 [124] 等，并在高温真实气体效应研究方面取得了一系列成果。飞行试验相比风洞试验能够完全反映出真实物理环境的影响，但其能够获取的数据有限，难以进行机理性研究工作。如 NASA 的无线电衰减测量(RAM)项目 [125] 测试了空气的电离特性和减轻无线电干扰的技术，得到了飞行器附近电子数密度分布。欧洲空间局(ESA)的试验飞行器 ELECTRE [126] 记录了再入过程中的气动力/热数据。数值模拟方法不…”

Section: 向力系数，(B)法向力系数，(c)俯仰力矩系数unclassified

Key issues in hypersonic vehicle aerodynamic design

An¹,

Lei²,

Su³

et al. 2021

Sci. Sin.-Phys. Mech. Astron.

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A hypersonic vehicle is a key competitive equipment direction of world aerospace power, and its aerodynamic design faces multiple technical challenges. This paper focuses on three key technical issues related to the aerodynamic design of a hypersonic vehicle, such as high lift -to-drag ratio aerodynamic design, prediction of the complicated physical effects in hypersonic flow around a body, and the ground-to-flight correlation of aerodynamic characteristics. Research progress is reviewed from the perspectives of the design method, prediction method, flow mechanism, and engineering applications. The technical difficulties in the engineering realization of a high lift -to -drag ratio waverider configuration, such as loading space and longitudinal stability, are analyzed with respect to the aerodynamic design. For the complex flow physics and prediction method, this paper summarizes the significance of key issues, including the boundary-layer transition, surface ablation, high-temperature real gas effect, and rare gas

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“…To validate the numerical solver, a case from the experimental investigation by Muylaert et al (1992) is selected. In the experiment, the surface heat flux referred to as ELECTRE was measured.…”

Section: Aerodynamic Heating Model Verificationmentioning

confidence: 99%

Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles

Liu

Zhu

et al. 2014

J. Zheijang Univ.-Sci.

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Abstract:Hypersonic vehicles subjected to strong aerodynamic forces and serious aerodynamic heating require more stringent design for an infrared window. In this paper, a finite element analysis is used to present the distributions of thermal and stress fields in the infrared window for hypersonic vehicles based on flowfield studies. A theoretical guidance is provided to evaluate the influence of aerodynamic heating and forces on infrared window materials. The aerodynamic heat flux from Mach 3 to Mach 6 flight at an altitude of 15 km in a standard atmosphere is obtained through flowfield analysis. The thermal and stress responses are then investigated under constant heat transfer coefficient boundary conditions for different Mach numbers. The numerical results show that the maximum stress is higher than the material strength at Mach 6, which means a failure of the material may occur. The maximum stress and temperatures are lower than the material strength and melting point under other conditions, so the material is safe.

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Standard model testing in the European High Enthalpy Facility F4 andextrapolation to flight

Cited by 21 publications

References 2 publications

Study on the Simulation Method of the Ground Test in the Arc-Heated Wind Tunnel

Study on the Simulation Method of the Ground Test in the Arc-Heated Wind Tunnel

Key issues in hypersonic vehicle aerodynamic design

Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles

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