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Experimental study of compressible boundary layer on a cone at angles of attack

Acta Mechanica Sinica 2009年第3期25卷 325-333页

作者： A.Maslov D.Bountin A.Shiplyuk A.Sidorenko Q.Shen Z.Bi Khristianovich Institute of Theoretical and Applied Mechanics(ITAM)and Novosibirsk State University China Academy of Aerospace Aerodynamics(CAAA)

Experimental study was conducted for boundarylayers on a sharp 5° half-angle cone of 400mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel （ITAM） at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0°, 2°, 3° and 4° angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer （second mode） have been detected.

关键词： compressible boundary layer Transition,Experimental study

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Analytical solutions to a compressible boundary layer problem with heat transfer

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Journal of University of Science and Technology Beijing 2004年第2期11卷 120-122页

作者： LiancunZheng XinxinZhang JichengHe AppliedScienceSchool UniversityofScienceandTechnologyBeijingBeijing100083China MechanicalEngineeringSchool UniversityofScienceandTechnologyBeijingBeijing100083China ThermalEngineeringDepartment NortheasternUniversityShenyang110006China

The problem of momentum and heat transfer in a compressible boundary layerbehind a thin expansion wave was solved by the application of the similarity transformation and theshooting technique. Utilizing the analytical expression of a two-point boundary value problem formomentum transfer, the energy boundary layer solution was represented as a function of thedimensionless velocity, and as the parameters of the Prandtl number, the velocity ratio, and thetemperature ratio.

关键词： compressible boundary layer momentum and heat transfer analytical solution

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Mathematical Formulation of Bubble Formation after compressible boundary layer Separation: Preliminary Numerical Results

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Open Journal of Fluid Dynamics 2022年第4期12卷 304-320页

作者： Michail A. Xenos Section of Applied and Computational Mathematics Department of Mathematics University of Ioannina Ioannina Greece

Laminar boundary layer (BL), under adverse pressure gradient, can separate. The separated shear layer reattaches to form a laminar separation bubble. Such bubbles are usually observed on gas turbine blades, on low Reynolds number wings and close to the leading edges of airfoils. Presence of bubbles has a weakening effect on the performance of a fluid device. The understanding of the prevailing mechanism of the separation bubble and ways to control it are essential for the efficient design of these devices. This is due to the significance of drag reduction in these various aerodynamic devices, such as gas turbines, re-entry space vehicles and airfoils. This study introduces a two-dimensional mathematical formulation of bubble formation after flow separation. The laminar BL equations with appropriate boundary conditions are dimensionalized using the Falkner-Skan transformation. Additionally, using the Keller-box method, the nonlinear system of partial differential equations (PDEs) is numerically solved. This study presents preliminary numerical results of bubble formation in low Mach numbers. These results reveal that after separation, a laminar bubble is formed in all studied cases, for Mach numbers, M = 0.2, 0.33 and 1.0. The flow after separation reverses close to the wall and finally reattaches downstream, in a new location. As the Mach number increases, this effect is more intense. After reattachment, the BL is again established in a lower energy level and the velocity field is substantially reduced, for all cases.

关键词： Laminar Separation Bubble compressible boundary layer Fluid Mechanics Computational Fluid Dynamics

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A NUMERICAL STUDY FOR SMALL AMPLITUDE T_S WAVES IN A SUPERSONIC boundary layer

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Applied Mathematics and Mechanics(English Edition) 2000年第12期21卷 1341-1344页

作者：袁湘江周恒 Department of Mechanics Tianjin University Tianjin P R China Research and Development Center of Aerodynamics of China Mianyang P R China

The propagation of the disturbance waves in a boundary layer at Mach number = 4.5 is studied by direct numerical simulation (DNS), using NND scheme, and different amplitudes A = 0.01, 0.001, 0.000 1 of the disturbance have been assumed. The numerical result shows that there might be shocklets induced in the boundary layer, even when the amplitude of disturbance wave is still small.

关键词： direct numerical simulation shocklet compressible boundary layer

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