Observational evidence for non-equilibrium ionization in the solar corona

We investigate whether temperature sensitive EUV line ratios can be used as observational signatures for the presence of non-equilibrium ionization in transition region plasma. We compute the total intensity of some EUV lines of carbon and oxygen expected from coronal loop models with a steady-state flow and which are known to have significant departures from ionization equilibrium, selecting lines whose intensity ratios are useful for deducing the electron temperature in the coronal plasma. We calculate the intensity ratios with and without the approximation of ionization equilibrium, in order to determine the effects of any deviations from equilibrium on the numerical values of the line ratios examined.     

Choice of flight conditions and modes of engine operation for its diagnostics

We consider a method for diagnostics of the engine flow passage technical status of a maneuverable aircraft operating in a wide range of altitudes and speeds; the behavior of measured parameter deviations from throttle characteristics and calculated characteristics of the flow passage units from their initial values is used for diagnostics. We present the methods for determining these deviations as well as flight conditions and engine operation modes at which diagnostics is made possible.     

基于直接力控制的阵风响应及阵风减缓研究

考察某无人机模型的阵风气动响应特性和基于直接力操纵的阵风减缓效果.在求解非定常Euler方程时引入“网格速度”方法模拟阵风边界条件,通过动态嵌套网格技术实现舵面运动.首先对NACA0006翼型迎角阶跃型阵风的气动力响应进行了验证计算,计算结果与理论结果、文献计算结果吻合良好.在此基础上对某无人机模型在迎角阶跃型、One-minus-cosine型阵风作用下的气动力响应过程进行了数值模拟,并分析评估了不同舵面运动方式对飞机气动性能的影响.最终研究比较了不同舵面运动方式下阵风气动响应的减缓效果.结果表明:通过合理设计舵面运动,可以有效达到抑制阵风引起的非定常气动干扰的目的.     

Transition prediction and sensitivity analysis for a natural laminar flow wing glove flight experiment

Natural laminar flow technology can significantly reduce aircraft aerodynamic drag and has excellent technical appeal for transport aircraft development with high aerodynamic efficiency. Accurately and efficiently predicting the laminar-to-turbulent transition and revealing the maintenance mechanism of laminar flow in a transport aircraft’s flight environment are significant for developing natural laminar flow wings. In this research, we carry out natural laminar flow flight experiments with different Reynolds numbers and angles of attack. The critical N-factor is calibrated as 9.0 using flight experimental data and linear stability theory from a statistical perspective, which makes sure that the relative error of transition location is within 5%. We then implement a simplified e^N transition prediction method with a similar accuracy compared with linear stability theory. We compute the sensitivity information for the simplified e^N method with an adjoint-based method, using the automatic differentiation technique (ADjoint). The impact of Reynolds numbers and pressure distributions on TS waves is analyzed using the sensitivity information. Through the sensitivity analysis, we find that: favorable pressure gradients not only suppress the development of TS waves but also decrease their sensitivity to Reynolds numbers; there exist three special regions which are very sensitive to the pressure distribution, and the sensitivity decreases as the local favorable pressure gradient increases. The proposed sensitivity analysis method enables robust natural laminar flow wings design.     

Extension of the low diffusion particle method for near-continuum two-phase flow simulations

The low diffusion (LD) particle method, proposed by Burt and Boyd, is modified for the near-continuum two-phase flow simulations. The LD method has the advantages of easily coupling with the direct simulation Monte Carlo (DSMC) method for multi-scale flow simulations and dramatically reducing the numerical diffusion error and statistical scatter of the equilibrium particle methods. Liquidor solid-phase particles are introduced in the LD method. Their velocity and temperature updating are respectively, calculated from the motion equation and the temperature equation according to the local gas properties. Coupling effects from condensed phase to gas phase are modeled as momentum and energy sources, which are respectively, equal to the negative values of the total momentum and energy increase in liquid or solid phase. The modified method is compared with theoretical results for unsteady flows, and good agreements are obtained to indicate the reliability of the one-way gas-to-particle coupling models. Hybrid LD-DSMC algorithm is implemented and performed for nozzle discharging gas-liquid flow to show the prospect of the LD-DSMC scheme for multi-scale two-phase flow simulations.     

Experimental research of wave resistance resonance for rough-wall plane channels

We experimentally confirmed the effect when the wave resistance of rough-wall plane channels, generated while the walls are streamlined by a supersonic gas flow, reaches the extreme values. The experiments were conducted on a differential setup by comparing the tests of flat and round sonic nozzles. The results of the experiment justified the developed method of calculating the wave resistance of the plane channel with sawtooth wall relief.     

固体火箭发动机燃烧室三维流场数值模拟

利用ＳＩＭＰＬＥ方法数值求解层流Ｎ－Ｓ方程，模拟了具有移动边界的固体火箭发动机燃烧室内的三维流场。网格划分采用交错网格技术，流场计算时不进行网格划分，而是直接读取网格点的值，将网格划分与流场计算分开，解决了现有计算机内存不够的问题，计算获得了满意结果。     

涡扇发动机加力燃烧室扩压器流场的数值计算

 本文用数值计算的方法得到了某型涡扇发动机加力燃烧室扩压器内的流场,与台架状态测得的实验数据基本吻合。研究了不同进口气流参数分布对扩压器流场的影响,计算了台架不同转速状态,不同飞行工况下扩压器内的流场。     

Time-dependent stresses in a beam under a load moving along its surface

We studied the time-dependent processes in a beam under the action of the load that is normal to its surface and moves with the constant velocity. It was found that the maximum stresses are realized in the fixed beam section at different moments of time depending on the travel speed of external load. With increasing the load movement velocity, the maximum stresses in the region of beam clamping are reduced, while the levels of local normal and shear stresses in the limits of its action increase more significantly approaching to the limiting values in accordance to the known experimental fact that at high rates the beam failure is caused by shear stresses.     

基于LBM-LES方法的多段翼型流场数值模拟

运用Lattice Boltzmann(LB)方法与Large Eddy Simulation(LES)结合的方法数值模拟研究了二维翼型绕流流场,其中,粒子速度模型采用D2Q9模型,松弛时间中对应的湍流粘性系数由Smagorinsky模型计算,网格生成方法采用无网格技术。对NACA0012翼型进行数值模拟,验证其有效性;为进一步研究其模拟复杂物体绕流的能力,以三段翼型30P30N为研究对象进行数值研究,计算出了给定攻角条件下的气动特性,并与实验值进行比较。计算结果表明,LBM-LES方法的计算结果能够与实验值一致,是一种可行、有效且较新的数值模拟方法。     

单列叶栅紊流流场有限分析数值研究

本文将有限分析方法用于曲线座标系上紊流 N-S方程数值计算,研究了高雷诺数时叶栅粘性紊流流场。有限分析方法在网格单元上对非线性偏微分程进行线化处理,在解析边界条件下求出线化偏微分方程的解析解,以此解构造离散方程。有限分析方法能够根据对流的方向和大小自动改变格式系数,并具有数值扩散小、精度高和稳定性好等优点。本文以 k-ε紊流模型模化紊流,以壁面函数方法处理近壁区流动参数。      

N-S方程有限分析数值研究

 本文将有限分析方法用于曲线座标系上紊流N-S方程的数值计算。分别计算了单列和串列叶栅内部流场,计算中采用了k-ε紊流模型和壁面函数。计算结果与试验结果相比较,吻合程度令人满意。有限分析方法在网格单元上对N-S方程进行线化处理,以解析边界条件作为约束,得出解析解,在解析解基础上构造离散代数方程。有限分析方法的最大特点是可以适应对流速度大小和方向,自动调整格式系数,因而具有数值扩散小和稳定性高等优点。     

Simulation of low-pressure water flow through the Laval nozzle taking into account evaporation on the basis of a two-temperature model of two-phase flow

A water flow through the Laval nozzle is studied using the model of the one-velocity two-temperature two-phase medium motion written on the basis of the Navier-Stokes equations. As an equation of state for the carrying phase, Tait??s equation is used. The vapor phase dynamics is described by the conservation equation for the concentration of bubbles having the critical radius, the Rayleigh-Lamb equation, and the equation of vapor pressure inside a bubble. The equations for the one-velocity two-temperature medium dynamics are solved by the Beam-Warming method. The explicit contraflow scheme is used to solve the Rayleigh-Lamb equation and the conservation equation for the bubble concentration. The solutions of the quasistationary type obtained for the plane Laval nozzle make it possible to estimate the local flow parameters and the rate of evaporation at with different values of counterpressure. We compare the solutions for the models of independent phase motion and those taking into account the interphase exchange of mass, impulse, and energy.     

Influence of periodic wakes on the development of a boundary layer

The flow in turbomachinery is strongly influenced by the rotor-stator interactions. It is known that the unsteadiness of the flow has for effect to advance the laminar-turbulent transition and to alter the heat transfer. The problem of the wake-boundary layer interaction has been studied experimentally by using a simplified geometrical configuration. The stator blade is simulated by a flat plate on which the development of the boundary layer disturbed by periodic wakes is observed. The wakes are generated by moving bars having a circular section, put upstream of the flat plate and running with a constant velocity in the wind of a low-speed tunnel. Numerical studies relating to the phenomenon of interaction are limited. Part of the experimental study has been carried out in a fully turbulent flow in order to avoid the problem of transition. These results are compared with those from a code solving the fully turbulent unsteady boundary layer equations.     

发动机短舱溢流阻力的数值模拟

 为分析发动机溢流阻力的产生原因并为进气道-发动机匹配研究提供一定的技术支持,以典型的发动机短舱为研究对象,分析了短舱上的进气道阻力,并详细介绍了相应溢流阻力的数值计算方法。在对发动机短舱外流模拟时,通过引入两个和发动机参数相关的数值边界条件,即一个是定流量的发动机进气道入流边界,另一个是定总温总压的发动机喷流边界,避免了对发动机复杂内流的模拟。利用NACA-1-81-100发动机进气道作为标准算例,验证了数值方法的可行性。通过模拟发动机短舱在不同工作流量下的流动,认为发动机短舱的溢流阻力产生归因为溢流造成的发动机外表面的阻力变化,以及捕获流管变细导致的附加阻力增加。     

基于流场感知的小型飞行器姿态控制

小型飞行器由于外形尺寸等限制很难实现理想的姿态控制，而自然界中的鸟类却可以完成高质量的飞行，原因是它们能够获得自身周围的气流信息。受这些自然现象的启发，设计了一个基于流场感知的小型飞行器姿态控制系统。通过流场感知的气流信息（压力和剪应力）可以计算出气动力和力矩。建立了一种小型飞行器的非线性三轴姿态动力学模型，将力矩信息引入姿态运动，然后利用非线性模型预测控制来设计姿态控制器。与传统的控制方法相比，这种新型控制方法不需要从气动实验获得的先验信息，所用的参数都是由在线测量得到的数据计算得出的，因此能及时感知外界环境变化并减少响应时间。仿真结果表明，该控制方法可以提高小型飞行器在复杂流场环境下姿态控制系统的性能。     

Planetary Dynamos from a Solar Perspective

Direct numerical simulations of the geodynamo and other planetary dynamos have been successful in reproducing the observed magnetic fields. We first give an overview on the fundamental properties of planetary magnetism. We review the concepts and main results of planetary dynamo modeling, contrasting them with the solar dynamo. In planetary dynamos the density stratification plays no major role and the magnetic Reynolds number is low enough to allow a direct simulation of the magnetic induction process using microscopic values of the magnetic diffusivity. The small-scale turbulence of the flow cannot be resolved and is suppressed by assuming a viscosity far in excess of the microscopic value. Systematic parameter studies lead to scaling laws for the magnetic field strength or the flow velocity that are independent of viscosity, indicating that the models are in the same dynamical regime as the flow in planetary cores. Helical flow in convection columns that are aligned with the rotation axis play an important role for magnetic field generation and forms the basis for a macroscopic α-effect. Depending on the importance of inertial forces relative to rotational forces, either dynamos with a dominant axial dipole or with a small-scale multipolar magnetic field are found. Earth is predicted to lie close to the transition point between both classes, which may explain why the dipole undergoes reversals. Some models fit the properties of the geomagnetic field in terms of spatial power spectra, magnetic field morphology and details of the reversal behavior remarkably well. Magnetic field strength in the dipolar dynamo regime is controlled by the available power and found to be independent of rotation rate. Predictions for the dipole moment agree well with the observed field strength of Earth and Jupiter and moderately well for other planets. Dedicated dynamo models for Mercury, Saturn, Uranus and Neptune, which assume stably stratified layers above or below the dynamo region, can explain some of the unusual field properties of these planets.     

顶部喷气对高速轴流压气机性能及流场的影响

喷气是提高压气机稳定工作裕度的有效措施之一。采用数值模拟方法研究了顶部喷气对某轴流压气机气动性能的影响。数值计算所获得实壁机匣总性能与其试验结果相吻合。喷气数值计算结果表明，转子上游约30％轴向弦长处的喷气推迟了失速的发生。通过详细地分析顶部喷气对压气机顶部区域流场结构的影响，揭示了其扩稳机理。     

化学非平衡喷管流计算方法的研究

本文提供了考虑化学反应非平衡和振动非平衡的喷管流动计算方法。在忽略扩散、粘性和热传导及辐射损失的假设下，得到完全气体一维定常流动方程，再加上振动能松驰方程和化学反应速率方程即可数值积分求解。采用扰动法得到接近平衡流的一组积分初值。采用“逆积分方法”求解通过喉道。计算结果是令人满意的。     

General rules for signal flow graph modeling and analysis of dc-dc converters

Signal flow graph (SFG) nonlinear modeling approach is well known for modeling dc-dc converters. However, all possible SFGs of a given dc-dc converter system will not yield the generalized graph. A systematic procedure and guidelines for developing unified flow graph models of the dc-dc boost converters, from which complete behavior can be determined is presented. Usefulness of the proposed method is demonstrated through examples. As an illustration a 2-cell cascade boost and interleaved boost converter systems are taken as examples. Derivation of large, small-signal and steady-state models from generalized flow graph is also demonstrated. Large-signal model is developed and programmed in TUTSIM simulator. Large-signal, responses against supply and load disturbances are obtained. Experimental observations are provided to validate the proposed algorithm.