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Investigation of thermal protection system by forward-facing cavity and opposing jet combinatorial configuration

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Chinese Journal of Aeronautics 2013年第2期26卷 287-293页

作者： Lu Haibo Liu Weiqiang Science and Technology on Scramjet Laboratory National University of Defense Technology Nanjing Artillery Academy

This paper focuses on the usage of the forward-facing cavity and opposing jet combinatorial configuration as the thermal protection system （TPS） for hypersonic vehicles. A hemispherecone nose-tip with the combinatorial configuration is investigated numerically in hypersonic free stream. Some numerical results are validated by experiments. The flow field parameters, aerodynamic force and surface heat flux distribution are obtained. The influence of the opposing jet stagnation pressure on cooling efficiency of the combinatorial TPS is discussed. The detailed numerical results show that the aerodynamic heating is reduced remarkably by the combinatorial system. The recirculation region plays a pivotal role for the reduction of heat flux. The larger the stagnation pressure of opposing jet is, the more the heating reduction is. This kind of combinatorial system is suitable to be the TPS for the high-speed vehicles which need long-range and long time flight.

关键词： Aerodynamic heating Forward-facing cavity Hypersonic flow opposing jet Thermal protection system

Numerical investigation on properties of attack angle for an opposing jet thermal protection system

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Chinese Physics B 2012年第8期21卷 289-294页

作者：陆海波刘伟强 Science and Technology on Scramjet Laboratory National University of Defense Technology

The three-dimensional Navier Stokes equation and the k-ε viscous model are used to simulate the attack angle characteristics of a hemisphere nose-tip with an opposing jet thermal protection system in supersonic flow conditions. The numerical method is validated by the relevant experiment. The flow field parameters, aerodynamic forces, and surface heat flux distributions for attack angles of 0°, 2°, 5°, 7°, and 10° are obtained. The detailed numerical results show that the cruise attack angle has a great influence on the flow field parameters, aerodynamic force, and surface heat flux distribution of the supersonic vehicle nose-tip with an opposing jet thermal protection system. When the attack angle reaches 10°, the heat flux on the windward generatrix is close to the maximal heat flux on the wall surface of the nose-tip without thermal protection system, thus the thermal protection has failed.

关键词： properties of attack angle opposing jet thermal protection system supersonic vehicle,computer simulation

Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle

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Journal of Zhejiang University-Science A(Applied Physics & Engineering) 2020年第9期21卷 761-769页

作者： Bin-xian SHEN Hong-peng LIU Wei-qiang LIU China Computational Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 621000China Science and Technology on Scramjet Laboratory College of Aerospace Science and EngineeringNational University of Defense TechnologyChangsha 410073China

Flying condition with angle of attack is inevitable in a hypersonic vehicle,and it may influence the thermal protection system(TPS)performance of opposing jet and its combinations.A 3D Navier–Stokes equation and shear stress transfer(SST)k-ωmodel with compressible correction are employed to simulate the angle of attack characteristics of a blunt body with opposing jet and platelet transpiration *** flowfield and heat flux transfer for angles of attack 0°,3°,6°with jet pressure ratio PR=0.1 and 0°,6°,12°with PR=0.2 are *** results show that the flowfield is no longer symmetrical with the effect of the angle of *** flowfield and heat transfer in windward and leeward performed *** recompression shock wave in windward is strengthened,which increases local temperature and strengthens heat *** opposing jet fails in thermal protection when the angle of attack reaches critical value;however,the critical angle of attack can be promoted by increasing ***,the transpiration gas can strengthen the cooling efficiency of windward,thereby,increasing the critical angle of attack.

关键词： Thermal protection opposing jet Platelet transpiration Angle of attack

A New Method of Thermal Protection by opposing jet for a Hypersonic Aeroheating Strut

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Journal of Thermal Science 2017年第3期26卷 282-288页

作者： QIN Jiang NING Dongpo FENG Yu ZHANG Junlong FENG Shuo BAO Wen Harbin Institute of Technology

This paper presents the numerical investigation of thermal protection of scramjet strut by opposing jet in supersonic stream of Mach number 6 with a hydrogen fueled scramjet strut model using CFD software. Simulation results indicate that when a small amount of fuel is injected from the nose of the strut, the bow shock is pushed away from the strut, and the heat flux is reduced in the strut, especially at the leading edge. opposing jet forms a recirculation region near the nozzle so that the strut is covered with low temperature fuel and separated from free stream. An appropriate total pressure ratio can be used to reduce not only aerodynamic heating but also the drag of strut. It is therefore concluded that thermal protection of scramjet strut by opposing jet is one of the promising ways to protect scramjet strut in high enthalpy stream.

关键词： thermal protection scramjet strut opposing jet

Experimental and numerical investigation on opposing plasma synthetic jet for drag reduction

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Chinese Journal of Aeronautics 2022年第8期35卷 75-91页

作者： Wei XIE Zhenbing LUO Yan ZHOU Wenqiang PENG Qiang LIU Dengpan WANG College of Aerospace Engineering National University of Defense TechnologyChangsha 410073China Beijing Special Engineering Design and Research Institute Beijing 100000China

Experimental and numerical studies are carried out to validate the potential of opposing Plasma Synthetic jet(PSJ)for drag reduction for a ***,flow field changes of opposing PSJ are analyzed by comparing the experimental schlieren images and simulation results in a supersonic free stream of Mach number *** PSJ is a kind of unsteady pulsed jet,the shock standoff distance increases initially and then decreases under the control of PSJ,which corresponds to the change of the strength of ***,the amount of drag reduction of the hemisphere increases initially and then *** is found that there is a short period of“drag rise”during the formation of PSJ before the drag reduction,which is induced by the generation of normal shock waves and the area difference of the cavity wall of PSJ Actuator(PSJA).Secondly,the effects of five parameters,including exit diameter,discharge energy of PSJA,Mach number,static pressure of incoming flow and angle of attack,on drag reduction of opposing PSJ were studied in detail by using numerical *** is found that the Maximum Pressure Ratio(MPR)has a significant impact on the average drag reduction for a configuration-determined *** the configuration selected in this study,the flow field of opposing PSJ shows typical Short Penetration Mode(SPM)in a control cycle of PSJ when the MPR is less than ***,the flow field shows typical Long Penetration Mode(LPM)at some time when the MPR is bigger than *** better drag reduction is achieved in this case.

关键词： Drag reduction opposing jet Parameter study Plasma synthetic jet(PSJ) Supersonic flow

Numerical Study on Combined Thermal Protection System of the Hypersonic Vehicle

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Numerical Study on Combined Thermal Protection System of the...