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Stagnation temperature effect on the conical shock with application for air

Chinese Journal of Aeronautics 2018年第4期31卷 672-697页

作者： Toufik ELAICHI Toufik ZEBBICHE Aeronautical Sciences Laboratory Institute of Aeronautics and Space Studies University SAAD Dahlab of Blida 1B.P.270

The aim of this work is to realize a new numerical program based on the development of a mathematical model allowing determining the parameters of the supersonic flow through a conical shock under hypothesis at high temperature, in the context of correcting the perfect gas model. In this case, the specific heat at constant pressure does not remain constant and varies with the increase of temperature. The stagnation temperature becomes an important parameter in the *** mathematical model is presented by the numerical resolution of a system of first-order nonlinear differential equations with three coupled unknowns for initial conditions. The numerical resolution is made by adapting the higher order Runge Kutta method. The parameters through the conical shock can be determined by considering a new model of an oblique shock at high temperature. All isentropic parameters of after the shock flow depend on the deviation of the flow from the transverse direction. The comparison of the results is done with the perfect gas model for low stagnation temperatures, upstream Mach number and cone deviation angle. A calculation of the error is made between our high temperature model and the perfect gas model. The application is made for air.

关键词： Calorically imperfect gas Conical shock High temperature Numerical integration oblique shock Perfect gas model Runge Kutta method Supersonic flow

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Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

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Advances in Aerodynamics 2022年第1期4卷 569-598页

作者： Tamal Jana Mrinal Kaushik Department of Aerospace Engineering JAIN(Deemed-to-be University)Bangalore560069India Department of Aerospace Engineering Indian Institute of Technology KharagpurKharagpur721302India

The primary focus of the present survey is to categorize the results of various investigations on the shock/Boundary-Layer Interactions(SBLIs),their repercussions,and the effective ways to control *** interactions of shock waves with the boundary layer are an important area of research due to their ubiquity in several applications ranging from transonic to hypersonic ***,there is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain *** this in mind,this article presents some key features of the physical nature of SBLIs,their consequences,and the control techniques in a sequential manner;in particular,the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail.

关键词： oblique shock Boundary layer Separation bubble Surface bump Porous cavity Micro-vortex generator(MVG) Plasma jet

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SCRAMJET INLET MULTI-OBJECTIVE OPTIMIZATION BASED ON RESPONSE SURFACE METHODOLOGY

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Transactions of Nanjing University of Aeronautics and Astronautics 2007年第3期24卷 205-210页

作者：李健谷良贤西北工业大学航天学院

The uniform design and response surface methodology （RSM） are applied to the multi-objective optimization of a 2-D mixed compression scramjet inlet. The set of experimental design points on the design space is selected by the uniform design, and the inlet performance is analyzed by computational fluid dynamics （CFD）. Then complete quadratic polynomial response surface approximation models are constructed based on the performance analysis results and then used to replace theoriginal complex inlet performance model. The optimization is conducted using a multi-objective genetic algorithm NSGA-Ⅱ, and the Pareto optimal solution set is obtained. Results show that the uniform design and RSM can reduce the computational complexity of numerical simulation and improve the optimization efficiency.

关键词： scramjet inlet response surface methodology oblique shock multi-objective optimization

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