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Thermophysics and Aeromechanics

2017 year, number 6

Gas-dynamic problems in off-design operation of supersonic inlets (review)

V.I. Zvegintsev

Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: supersonic flow, inlet, air-breathing engine, flow deceleration, shock waves, start/unstart, backpressure
Pages: 807–834
Abstract >>
Modern concepts of operation of supersonic inlets of high-velocity air-breathing engines are analyzed. It is demonstrated that the flow in the engine duct becomes extremely complicated in off-design modes of inlet operation, which can lead to unpredictable consequences, in particular, to inlet unstart. The term “inlet unstart” is considered in the present paper as a synonym of the absence of theoretical understanding and prediction of gas-dynamic phenomena. Various approaches are proposed to ensure self-regulation of the inlet-combustor system for air-breathing engines. Possible directions of further research are indicated for the purpose of stable operation of inlets in a wide range of flight conditions.

DOI: 10.1134/S0869864317060014


Development of a coupled NS-DSMC method for the simulation of plume impingement effects of space thrusters

Z. Yang1,2, Z.-Y. Tang3, G.-B. Cai1, and B.-J. He1
1School of Astronautics, Beihang University, Beijing, China
2China Academy of Space Technology, Beijing, China
3Beijing Institute of Spacecraft Environment Engineering, Beijing, China
Keywords: coupled NS-DSMC method, continuum-rarefied transitional flow, vacuum plume ef-fect, space thrusters
Pages: 835–847

Abstract >>
A coupled NS-DSMC method possessing adapted-interface and two-way coupling features is studied to simulate the plume impingement effects of space thrusters. The continuum-rarefied interface is determined by combining KnGL and Ptne continuum breakdown parameters. State-based coupling scheme is adopted to transfer information between continuum and particle solvers, and an overlapping grid technique is investigated to combine structured-grid NS code and Cartesian-grid DSMC code to form the coupled solver. Flow problem of a conical thruster plume impinging on a cone surface is simulated using the coupled solver, and the simulation result is compared with experimental data, which proves the validity of the proposed method. Plume flow while the ascent stage of lunar module lifting off in lunar environment is also computed by using the present coupled NS-DSMC method to demonstrate its capability. The whole flow field from combustion chamber to the vacuum environment is obtained, and the result reveals that special attention should be paid to the plume aerodynamic force at the early stage of launching process.

DOI: 10.1134/S0869864317060026