实验流体力学

Investigation of possibilities in developing dual-mode scramjets

LE Jia-ling, HU Yu-li, LIU Ling

2000, 14(1): 1-12. doi: 10.3969/j.issn.1672-9897.2000.01.001

Abstract(142) PDF(12)

Abstract:

Verification of the numerical investigations of convergent inlet

2000, 14(1): 13-22.

Abstract(74) PDF(6)

Abstract:
The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area,which was called a convergent inlet,are presented in this paper.It is shown that the use of this inlet configuration allows one to reduce the drag and thermal protection of surfaces of a hypersonic engine within the entire range of flight velocities.This is achieved by decreasing the inclination of extemal compression surfaces and reducing the area of the inlet duct and combustor walls.The inlet configuration was constructed on the basis of gas dynamic design methods using the flows of lower dimension.The calculations were performed within the framework of inviscid gas model by the method of finite volumes.The flow and inlet characteristics,taking account of viscosity,were also calculated using the boundary layer equations.The numerical algorithm was verified by calculated and experimental data for a finite-width wedge and extemal compression surface of a convergent inlet.The experimental studies were performed within the Mach number range from 2 to 10.7 and Reynolds number based on the model inlet height of Re=(1~5)106. The numerical and experimental results are in good agreement.These results are also compared with the data for traditional 2D inlets.

The study of characteristics of three-dimensional inlets with flat walls

2000, 14(1): 23-31.

Abstract(103) PDF(3)

Abstract:
Results of an experimental study of 3D inlets and the scramjet module are presented.The scramjet module consists of an inlet and a combustion chamber.The module is designed to study the flow structure,to obtain the inlet characteristics, and to study the mutual effects of the combustor and the inlet,fule ignition and combustion (hydrogen and hydrocarbon fuels). The tests was conducted in the blowdown wind tunnel at Mach numbers from 2 to 6 and unit Reynolds numbers from 8 to 54 million and in the hot-shot wind tunnel at Mach numbers M=6 and 7.2 and unit Reynolds numbers from 10 to 32 million (Tt=1500~2500K).

Methodical features of testing gas-dynamic models with combustion in short-duration facilities

2000, 14(1): 32-42.

Abstract(82) PDF(2)

Abstract:
Methodical features of testing gas-dynamic models with combustion in high-enthalpy short-duration facilities are presented. Based on the experience in organization of this kind of work, which has been accumulated at ITAM SB RAS, the specific features of model arrangements for solution of various problems with combustion, measurement of thrust-aerodynamic characteristics, measurement of pressure and heat fluxes in the engine duct, etc., are described. It is shown that hot-shot wind tunnels with the test time of 50~200 ms are reliable tools for solving combustion problems.

Study and application of hydrocarbon-fueled supersonic combustion

SITU-Ming

2000, 14(1): 43-50. doi: 10.3969/j.issn.1672-9897.2000.01.005

Abstract(99) PDF(3)

Abstract:

Experimental study of supersonic combustion of kerosene in dual combustor

SUN Ying-ying, SITU Ming, WANG Chun, HAN Zhao-yuan

2000, 14(1): 51-56. doi: 10.3969/j.issn.1672-9897.2000.01.006

Abstract(170) PDF(4)

Abstract:

An investigation of later period of primary breakup in axisymmetric dissemination of liquid ring

CAI Qing-jun, HAN Zhao-yuan, WAN Qun, ZHANG Shou-qi