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An integration method based on a novel combined flow for aerodynamic configuration of strutjet engine

Chinese Journal of Aeronautics 2021年第9期34卷 156-167页

作者： Longsheng XUE Chuan CHENG Chengpeng WANG Keming CHENG College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China Aerospace System Engineering Shanghai Shanghai 201100China

In this paper a novel design method of aerodynamic configuration is proposed to integrate forebody,strut and inlet for strutjet engine,and a model at design point of Mach number6 is generated to investigate the aerodynamic performance by both simulations and *** basic flow field employed by proposed method is a combined flow named IBB,which is combined by Internal Conical Flow A(ICFA),truncated Busemann flow I(BI)for external section,and truncated Busemann flow II(BII)for internal *** model configuration is generated by streamline tracing method from basic flow field,in which the forebody section is traced from ICFA and BI flows,and the inlet as well as strut section is traced from BII *** simulations in Mach number 4,5,and 6 demonstrate uniform starting flow fields with relatively high total pressure recovery,which agree well with experiments in wind ***,in low Mach number cases,this inlet could start at Mach number 3 while it is unstarted at Mach number 2.7;in high Mach number cases,a uniform flow could still exist in Mach number 6.5 while a relatively strong shock wave boundary layer interaction is found in cowl area of Mach number 7 case,indicating the inlet designed by proposed method works in a relatively wide Mach number range.

关键词： Airframe-propulsion integration Busemann flow Combined flow hypersonics Wind tunnel test

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Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics

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Acta Mechanica Sinica 2021年第3期37卷 422-433,I0002页

作者： C K.Yuan Z.L.Jiang Institute of Mechanics Chinese Academy of SciencesBeijing 100190China University of Chinese Academy of Sciences Beijing 100190China

Hypersonic air-breathing propulsion is one of the key techniques for future aviation and the ground aerodynamic testing for full scale test models with sufficient test time at flight conditions is of fundamental importance for verifying hypersonic air-breathing *** on the backward detonation-driven concept,the hypersonic flight-duplicated shock tunnel(or JF-12 shock tunnel)has been successfully constructed and *** facility is capable of reproducing airflow for Mach numbers ranging from 5 to 9 at an altitude of 25-50 km,with a test duration of more than 100 *** quantify the performance of the shock tunnel,experiments were conducted to investigate the aerodynamic characteristics of the test flows and the effects of several critical techniques that play important roles in the operation of the shock *** stagnation pressure was constant within士5%and the average stagnation pressure varied by less than 0.048%/*** variation of the stagnation pressure in repeated experiments is less than 2.0%,indicating the good repeatability of the wind *** non-uniformity of the Mach number in the core flow field at the nozzle exit was within士2.5%.Additional,a uniform flow field is established upstream of the nozzle *** axial gradients of the flow field are small since the Mach number varies less than 1.7%/*** regarding the ignition technology,diaphragm ruptures,detonation driver capacity,incident shock-wave decay,and tunnel operation mode are also *** findings of this study are not only helpful for operating the shock tunnel,but can also assist the future development of hypersonic wind tunnels.

关键词： hypersonics Shock tunnels Flow characteristics

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Optical Diagnostics in Rarefied Flows

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Chinese Journal of Aeronautics 2006年第2期19卷 151-159页

作者： Jean-Pierrer TARAN ONERA DSG/RS 92320ChtillonFrance

This article reviews the instrumental developments accomplished at ONERA in order to perform precise non-intrusive measurements of hypersonic flows using laser- and electron-beam-based optical techniques. Point line of sight and imaging measurements are possible. Point measurements have been implemented with Electron Beam Fluorescence （EBF） using detection of X-ray radiation and Coherent anti-Stokes Raman Scattering （CARS）. When spatial resolution is not required, diode laser absorption spectroscopy yields results integrated along a line. EBF imaging using a high energy pulsed electron gun is also quite promising. Rotational and vibrational populations of nitrogen and nitric oxide have been measured in various hypersonic hyperenthalpic facilities, as well as rotational state-resolved velocities in shocks and boundary layers.

关键词： hypersonics optical measurements CARS EBF lasers absorption

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Oblique-mode breakdown in hypersonic and high-enthalpy boundary layers over a blunt cone

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Advances in Aerodynamics 2021年第1期3卷 413-427页

作者： Xianliang Chen Dongxiao Xu Song Fu School of Aerospace Engineering Tsinghua University100084 BeijingChina

The nonlinear analyses of the hypersonic and high-enthalpy boundary-layer transition had received little attention compared with the widely-studied linear *** this work,the oblique-mode breakdown,as one of the most available transition mechanisms,is studied using the nonlinear parabolized stability equations(NPSE)with consideration of the thermal-chemical non-equilibrium *** flow over a blunt cone is computed at a free-stream Mach-number of *** rope-like structures and the spontaneous radiation of sound waves are observed in the schlieren-like *** is also illustrated that the disturbances of the species mass and vibrational temperature near the wall are mainly generated by the product term of the wall-normal velocity disturbance and the mean-flow *** comparison to the CPG flow,the TCNE effects destabilize the second mode and push upstream the N factor *** higher growth rate of the oblique wave leads to stronger growth of the streamwise vortices and harmonic waves.

关键词： Boundary-layer transition hypersonics High-enthalpy flows

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Hypersonic Waverider Surface Development Using Aerodynamic Flow Around Conical Bodies

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Computer Aided Drafting,Design and Manufacturing 2006年第1期16卷 63-69页

作者： Najam-us-Saqib School of Astronuatics Beijing University of Aeronautics and Astronautics Beijing 100083 China

Developing the waverider based hypersonic vehicles is an inverse design process in which shape is developed from a known flow field by tracing of streamlines to form a stream surface. The flow field can be based on a solution of Taylor Maccoll equation for a specified shock or cone angle. This Paper discusses the development of waverider shapes for hypersonic reentry vehicles.

关键词： aerodynamic design hypersonics waveriders surface generation

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