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Boundary-layer Correction for the Streamline-traced Busemann Inlet

Author: ChenDongLiang
Tutor: LiangJianHan
School: National University of Defense Science and Technology
Course: Aeronautical and Astronautical Science and Technology
Keywords: Boundary layer correction Busemann inlet Streamline tracking Displacement thickness correction method Secondary correction
CLC: V211.48
Type: Master's thesis
Year: 2009
Downloads: 42
Quote: 2
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Abstract


Busemann inlet benchmark the Busemann inlet and flow line tracking as the research object, through theoretical analysis and numerical simulation method of combining internal steering compression hypersonic inlet type surface viscous correction method to carry out the research. Firstly baseline Busemann inlet this axisymmetric steering the compressed configuration. By contrast the the inviscid design baseline Busemann inlet in the inviscid condition and viscous conditions downstream field differences, analysis of the impact of the wall boundary layer on the inlet flow fields. The results show that the effect of the wall boundary layer, the inlet flow fields serious deviation from the inviscid design state, serious distortions in the flow field Neimahebo polymerization poor, can not form a clear end of the conical shock wave, the poor quality of the export flow field, flow loss. In contrast plate boundary layer correction method and literature central axis symmetric configuration correction method corrected results based on the displacement thickness correction method mentioned in the literature to explore, a detailed analysis of the various parameters of the amendment process, the correction results and improvements on the basis of the original method to obtain a complete correction ideas. By numerical simulation to verify the feasibility of the method, the correction effect is obvious, and compared the results of the literature has been some improvement, closer to the inviscid design flow field. The quadratic correction ideas boundary layer, thickening of the boundary layer with the boundary layer correction method to improve the flow inside the shock incident caused further improve the flow field, and get good results. Contrast to the No stick design flow line tracking Busemann inlet distinction inviscid conditions and sticky conditions downstream field wall boundary layer of the structure and performance of the inlet flow fields. The results show that the sticky conditions inlet flow is a serious deviation from the inviscid design state, the boundary layer is very substantial, serious change the shape of the mainstream, increasing the amount of the actual compression of the inlet. Messy waves in the flow field the isolator inlet flow field is very uneven. Convection wall correction method using modified line tracking the the Busemann inlet of the type face, and verified by numerical calculation. The corrected flow field wave system has been improved to a certain extent some characteristics closer inviscid design state, inlet compression level decreased, and the flow of isolated segments within the corner regions improved. Swept the amendment results in the lip area, and isolation of the flow field uniformity to be further improved, the boundary layer in three-dimensional conditions fix the problem needs further research.

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aerodynamics > Aircraft aerodynamics > Inlet
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