缅怀周培源老师

缅怀周培源老师彭桓武，何泽慧（中国科学院理论物理研究所，北京１０００８０）（中国科高能高能物理研究所，北京１０００３９）王大珩（中国科学院空间科学与应用研究中心，北京１０００８０）３０年代上半期，我们在清华大学物理系学习，周先生是教我们力学的启蒙老师...     

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Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow

The design of supersonic three-dimensional inlets using the V-shaped body forming a two-dimensional flow including an initial oblique shock wave and a subsequent isentropic compression wave is considered. Such a flow appears attractive for inlets design due to a possibility of obtaining high compression levels of external flow over the inlet ramp with small losses of the total pressure. Numerical computations of the flows around the designed configurations were carried out in design and off-design regimes using Euler code. The flow structure was identified, the aerodynamic characteristics of the inlets were determined. The investigation covers the range of supersonic speeds corresponding to the freestream Mach numbers M_∞= 1.8−2.5.     

Generation of a gas-discharge air plasma in a supersonic magnetohydrodynamic channel

A method for ionizing a supersonic air flow is developed to obtain a flow conductivity sufficient for a magnetohydrodynamic (MHD) interaction and generation of a magnetically induced current in a supersonic nozzle. The efficiencies of several (high-frequency, multiple-pulse high-voltage, and combined) methods for initiating a gas discharge used for ionizing air are compared. The supersonic air flow is ionized by a pulse-periodic high-voltage discharge producing an air plasma with a conductivity of up to 20 S/m. The experimentally obtained magnetically induced current of 0.1 A is smaller than the rated value owing to the Hall effect and the electrode voltage drop. The theoretical possibility of obtaining a magnetically induced current in a supersonic air flow is demonstrated; such currents can subsequently be used for controlling the flow in air inlets of aircraft.     

Gas-dynamic problems in off-design operation of supersonic inlets (<Emphasis Type="Italic">review</Emphasis>)

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.     

高超音速进气道粘性流场的分块计算

本文采用一种隐式迎风型TVD格式求解二维Navier—Stokes方程，使用分块技术数值模拟了某超音速进气道在飞行马赫数2．291和2.557两种状态下的流动，给出了该进气道的内外流场结构、捕获面积比、表面压力分布、总压恢复系数等等。     

超声速平板圆台突起物绕流实验和数值模拟研究

高速飞行器表面不可避免的存在突起物并形成复杂流场, 从而引起飞行器气动特性和热载荷的变化; 同时, 突起物是流动控制的重要方法之一, 合适的突起物形状及安装位置对于改善冲压发动机进气道性能有重要意义. 本文采用基于纳米粒子的平面激光散射技术(NPLS)研究了马赫3.0来流边界层为层流的平板上三个不同高度圆台突起物绕流流场, 主要关注了突起物后方的尾迹边界层, 并采用高精度的显式五阶精度加权紧致非线性格式(WCNS-E-5)离散求解Navier-Stokes方程模拟了该流场. 获得了超声速圆台绕流精细流场结构, 观察到突起物后方尾迹区域边界层发展的过程. 结合实验和数值模拟结果可以发现, 当圆台高度接近或者小于当地边界层厚度时, 突起物对边界层的扰动非常弱, 圆台后方尾迹边界层能够维持较长距离的层流状态, 在边界层转捩阶段也有清晰的发卡涡结构出现; 反之, 边界层受到的扰动明显增大, 在突起物后方很快发展为湍流; 风洞噪声对本文研究圆台引起的边界层扰动有一定影响, 实验获得的边界层转捩位置要比数值结果靠前. 基于NPLS流场图像, 采用间歇性方法分析了圆台突起物后方边界层的特性, 对于高度大于边界层厚度的圆台其间歇性曲线较为接近并且更加饱满, 边界层的脉动也更为强烈.     

On the question of starting conditions for frontal axisymmetric inlets tested in hot-shot wind tunnels

The work presents the results of an analysis of starting conditions for some frontal axisymmetric inlets of internal compression tested at freestream Mach numbers М = 3?8.4 in the hot-shot wind tunnels based at Khristianovich Institute of Theoretical and Applied Mechanics (ITAM). The results of these inlets test are compared with the data of numerical computations of inviscid, laminar, and turbulent flows carried out by the pseudo-unsteady method. There were determined the inlet throat areas limiting either with regard to the inlet starting or with regard to providing the maximally possible degree of geometric compression of the inlet-captured supersonic airstream at its deceleration in the already started inlet. Reshaping of computed flow patterns in the inlets depending on the variation of the minimal cross section of the inlet internal duct is analyzed.     

压力恢复系统超声速扩散段三维流场数值模拟

 采用数值模拟的手段，对压力恢复系统超声速扩散段三维流场进行研究。数值模拟使用LU分解法和NND差分格式求解全Navier-Stokes 方程，并加入了湍流模型。对得到的流场结构进行了分析，为下一步工作打下了基础。     

A quadrature-based LES/transported probability density function approach for modeling supersonic combustion

The joint-scalar probability density function (PDF) approach provides a comprehensive framework for large eddy simulation (LES) based combustion modeling. However, currently available stochastic approaches for solving the high-dimensional PDF transport equation can be error prone and numerically unstable in highly compressible shock-containing flows. In this work, a novel Eulerian approach called the direct quadrature method of moments (DQMOM) is developed for evolving the PDF-based supersonic combustion model. The DQMOM technique uses a set of scalar transport equations with specific source terms to recover the PDF. The new technique is coupled to a compressible LES solver through the energy equation. The DQMOM approach is then used to simulate two practical flow configurations: a supersonic reacting jet and a cavity-stabilized supersonic combustor. Comparisons with experimental data demonstrate the predictive accuracy of the method.     

分区拼接网格算法数值模拟超声速复杂流场

以分区拼接网格数值模拟方法为研究对象,对二阶Godunov方法在拼接网格中流场的数值模拟进行了研究,发展了适用于Godunov格式的通量守恒型算法,结合二阶Godunov有限体积法离散非定常Euler方程,数值模拟了捆绑火箭及航天飞机的超声速流场,计算结果正确描述了流场中的激波相交、反射等干扰特性.     

Investigation of annular supersonic inlets with isentropic compression

A technique for designing the supersonic annular inlets with isentropic deceleration surfaces is considered. The contour of an isentropic supersonic nozzle constructed by the method of characteristics for an inviscid gas flow with given uniform parameters at the inlet and at the outlet is used as the basic configuration of the inlet. The reversed flow of a viscous gas is computed with the aid of numerical techniques in the contour under consideration and the real operational characteristics of the obtained inlet of a fixed geometry are determined in the range of the conditions of its application. In the process of computations, the minimum cross-sectional sizes are selected, which ensure the inlet start without a detached bow shock at the entrance.