基于全局线性稳定性分析的翼尖双涡不稳定特征演化机理

相比于机翼产生的孤立翼尖涡，加装小翼之后的翼尖涡表现出双涡甚至多涡结构，并且呈现出更加复杂的不稳定特征。为揭示翼尖双涡结构不稳定特征及其演化机理，采用体视粒子图像测速（SPIV）技术和全局线性稳定性分析（LAS）方法对不同雷诺数和攻角下带双叉弯刀小翼的M6机翼产生的翼尖涡结构在尾迹区的不稳定特征进行研究。试验结果表明，对称布置的双叉弯刀小翼产生的翼尖涡包含上/下小翼产生的主涡（上/下主涡）结构，两者构成近似等强度的同转涡对，在相互靠近的同时以20 rad/s的角速度相互缠绕。对上/下主涡瞬时涡核位置的统计分析表明，翼尖涡摇摆幅值随流向位置逐渐增大，随雷诺数的增加而增大，随攻角的增加先增大后减小。对16倍弦长的尾迹截面处的翼尖双涡结构进行全局时间稳定性分析，不同工况下，上/下主涡最不稳定模态（模态P/模态S）的稳定性曲线变化规律与摇摆幅值的变化规律相一致，表明翼尖涡的摇摆源自于其内在的不稳定性特征。增加流向扰动波数，发现模态P切向波数逐渐增加；而模态S则是径向波数逐渐增加。不同工况下，模态P的切向波数为5~6，扰动波数分布在[2.75，5]的区间内，所对应的不稳定放大率均大于模态S，而不稳定放大率最大的模态扰动范围作用在上主涡的整个涡核区域，表明这种大切向波数的扰动模态在翼尖涡流控中的潜在价值，也意味着加装小翼会增加涡结构的个数，增强不稳定性的发展，有助于翼尖涡的快速失稳衰减。     

基于线性稳定性分析的翼尖涡摇摆机制

在涡不稳定性特征的影响下，翼尖涡会在尾迹中发生摇摆运动。为了揭示翼尖涡摇摆的本质原因以及发展机理，采用体视粒子图像测速（SPIV）技术和线性稳定性分析方法对不同雷诺数和迎角下NACA0015等直翼产生的翼尖涡在尾迹区的不稳定性特征及发展进行研究。结果表明：在1~6倍弦长的尾迹区内，翼尖涡存在摇摆现象，摇摆幅值随流向放大，且摇摆运动沿流向逐渐呈现出各向异性特征；在大迎角条件下，翼尖涡摇摆幅值随流向增长更快。采用线性稳定性分析方法，定量化分析翼尖涡的稳定性、空间/时间不稳定性放大率和扰动频率随流向的发展过程。结果显示，在雷诺数2.1×10⁵~3.5×10⁵范围内，翼尖涡均处于临界稳定状态，扰动频率为3~5 Hz。基于线性稳定性分析结果，发现在大迎角条件下翼尖涡时间/空间不稳定性放大率更大，解释了当迎角增大时翼尖涡摇摆幅值随流向增长更快的现象。另外，由线性稳定性分析得到的最不稳定模态显示翼尖涡的横向速度扰动具有明显的方向性，从而诱导翼尖涡产生摇摆运动；速度扰动方向的周期性变化则使翼尖涡摇摆区别于一维的随机振荡，而是表现为在各方向均含有分量且具有主频的摇摆运动。这种由不稳定性导致的速度扰动是翼尖涡摇摆的内在机制，其不稳定性放大率控制着摇摆幅值的增长速率，而其横向速度扰动的方向性与周期性则决定了翼尖涡的摇摆特征。     

Assessment and improvement of k-ω-γ model for separation-induced transition prediction

The purpose of this work is to improve the k-ω-γ transition model for separation-induced transition prediction. The fundamental cause of the excessively small separation bubble predicted by k-ω-γ model is scrutinized from the perspective of model construction. On the basis, three rectifications are conducted to improve the k-ω-γ model for separation-induced transition. Firstly, a damping function is established via comparing the molecular diffusion timescale with the rapid pressure-strain timescale. The damping function is applied to prevent the effective length scale from incorrect distribution near the leading edge of the separation bubble. Secondly, the pressure gradient parameter λ_ζ, is proposed as an indicator for local susceptibility to the separation instability. Additionally, λ_ζ,-based separation intermittency γ_sep is constructed to accelerate the substantial growth of turbulent kinetic energy after flow separation. The improved model appropriate for both low- and high-speed flow has been calibrated against a variety of diverse and challenging experiments, including the subsonic T3L plate, Aerospatial A airfoil, transonic NLR-7301 airfoil and deformed hypersonic inflatable aerodynamic decelerator aeroshell. The improved model is strictly based on local variables and Galilean invariance. Besides, the proposed improvement for k-ω-γ model can be fairly convenient to incorporate into other existing intermittency-based transition models.     

气膜内冷通道高度对气膜孔流量系数的影响

以一种基于旋流增益的强化换热技术为研究对象,对狭小受限的气膜孔内冷通道中气膜孔的流量系数开展了试验研究.试验中通过改变气膜孔雷诺数Re(4800～26000)、吹风比M(0.36～2.74)、无量纲冷却通道高度h/d(0.33～2.0)等参数,研究了狭小空间的几何结构、流动参数等对单排气膜孔平均流量系数Cd的影响,并得...     

分枝模态综合法的逆问题

 本文基于李兹分析论述了分枝模态综合法的逆问题,即结构的一个分枝系统的模态特性如何利用结构和其它分枝系统的模态特性而识别出来。其分析方法可应用于结构动态设计和结构模型修改问题。     

Microphysics of Cosmic Plasmas: Hierarchies of Plasma Instabilities from MHD to Kinetic

In this article, we discuss the idea of a hierarchy of instabilities that can rapidly couple the disparate scales of a turbulent plasma system. First, at the largest scale of the system, L, current carrying flux ropes can undergo a kink instability. Second, a kink instability in adjacent flux ropes can rapidly bring together bundles of magnetic flux and drive reconnection, introducing a new scale of the current sheet width, ?, perhaps several ion inertial lengths (δ _i ) across. Finally, intense current sheets driven by reconnection electric fields can destabilize kinetic waves such as ion cyclotron waves as long as the drift speed of the electrons is large compared to the ion thermal speed, v _D ?v _i . Instabilities such as these can couple MHD scales to kinetic scales, as small as the proton Larmor radius, ρ _i .     

Experimental investigation and correlation development of jet impingement heat transfer with two rows of aligned jet holes on an internal surface of a wing leading edge

Extensive experimental studies on the heat transfer characteristics of two rows of aligned jet holes impinging on a concave surface in a wing leading edge were conducted, where50000 Rej 90000, 1.74 H/d 27.5, 66° a 90°, and 13.2 r/d 42.03. The finding was that the heat transfer performance at the jet-impingement stagnation point with two rows of aligned jet holes was the same as that with a single row of jet holes or the middle row of three-row configurations when the circumferential angle of the two jet holes was larger than 30°. The attenuation coefficient distribution of the jet impingement heat transfer in the chordwise direction was so complicated that two zones were divided for a better analysis. It indicated that: the attenuation coefficient curve in the jet impingement zone exhibited an approximate upside-down bell shape with double peaks and a single valley; the attenuation coefficient curve in the non-jet impingement zone was like a half-bell shape, which was similar to that with three rows of aligned jet holes; the factors,including Rej, H/d and r/d, affected the attenuation coefficient value at the valley significantly.When r/d was increased from 30.75 to 42.03, the attenuation rates of attenuation coefficient increased only by 1.8%. Consequently, experimental data-based correlation equations of the Nusselt number for the heat transfer at the jet-impingement stagnation point and the distributionof the attenuation coefficient in the chordwise direction were acquired, which play an important role in designing the wing leading edge anti-icing system with two rows of aligned jet holes.     

Who is who in Algol-land ?- Part I -

We computed the evolution through case A mass transfer for 8 systems with mass of the primary equal to 3 and 5 M₀, mass ratios 0.7 and 0.9, and different periods. To this we added similar results from Packet (1988) for M_i = 9 M₀, q_i = 0.6, P_i = 1.62 d.During the mass transfer two competing mechanisms in the gainer decide on the evolution of the system: the rejuvenation of this star as the increasing convective core mixes fresh hydrogen into the inner regions, and the acceleration of nuclear burning, responding to the increasing mass.In all the cases the net result is a faster decrease of the central hydrogen content compared to the mass losing star. The secondary fills its own critical Roche lobe and reversed mass transfer starts.From our results and those of Nakamura and Nakamura (1984), we find that reversed mass transfer occurs after core hydrogen burning of the secondary (case A₁B₂) approximately for periods larger than 1 d (M_1i = 3 M₀) to 2 d (M_1i = 13.4 M₀). For smaller periods this happens before the gainer ends its core hydrogen burning (case A₁A₂).     

合成射流大攻角非对称涡控制的试验研究

利用合成射流对细长旋成体大攻角非对称涡控制进行了研究,基于合成射流激励器设计了一频率高达1kHz的非定常小扰动控制机构,并将其成功应用于大攻角非对称涡主动流动控制。应用天平测力和七孔探针流场测试技术,研究了合成射流非定常小扰动电压和频率对非对称涡的控制特性和规律。结果表明,采用合成射流能够完全消除背涡的非对称性,扰动频率是影响非对称涡控制的一个关键参数,高频扰动下模型背风区非对称涡结构趋于无控制流态。且文中结果发现,当攻角α=57.5°、非定常小扰动频率fs=150Hz时,即可将非对称涡完全控制成为对称涡。     

Plasma transport during substorm growth phase and relation to breakup

For <_bi,_be, the electron and ion bounce frequencies, the response of a plasma to an externally applied electromagnetic perturbation is nonlocal. This implies, via the quasi-neutrality equation, the development of an electrostatic potential which is constant for a given magnetic field line. In the near equatorial region the corresponding potential electric field is shown to oppose the effect of the induced electric field associated with the externally applied perturbation. Thus the effect of the induced electric field is partially shielded; the total azimuthal electric field (i.e. induced plus potential) tends to be small, which explains why the radial flow velocity is slow during quasi-steady conditions prevailing during the growth phase and after the active phase. The nonlocal response of the plasma also leads to the development of a parallel current that may generate current driven Alfvén (CDA) waves, which mode convert into shear Alfvén (SA) waves. CDA/SA waves are systematically observed at early breakup; they grow very fast and produce a parallel diffusion of electrons. As soon as the diffusion time is shorter than the bounce time (_d<_b), the nonlocal response vanishes. Thus the shielding disappears, and an enhanced transport is restored at the rate fixed by the induced electric field alone. We show that fast flows effectively occur when CDA waves have enough power to diffuse electrons (over _d<_b). Electron parallel diffusion also leads to an interruption of the parallel current and therefore to a disruption of the perpendicular current.     

Assessment of gas temperature fluctuations in the GTE combustion chamber exit section at generalizing experimental data on fuel combustion efficiency

It is suggested that gas composition at every point of the combustion chamber exit section be characterized by the temperature values T _i (“ideal” temperature) corresponding to the local values of the air-to-fuel coefficient α _i under complete fuel combustion (ν _comb ≈ 1). It is assumed that the values of T _i are distributed over the exit section area (gas mass) linearly and the values of T _imax and T _imin can be determined by the experimental data on the gas temperature fields in the combustion chambers. The distribution of temperatures T _i is used when it is necessary to generalize the experimental data on fuel combustion efficiency in GTE combustion chambers.     

试验研究旋流数对燃烧室气动性能的影响

为了深入了解双级轴向旋流器的旋流数变化对模型环形燃烧室内气流结构与气动性能的影响,采用粒子图像速度仪(PIV)对燃烧室内冷态和液雾燃烧流场进行测量,试验研究在冷、热态情况下不同旋流数对模型燃烧室内回流区的尺寸、平均速度(u,v)、脉动速度(U<,rms>,V<,rms>)以及雷诺剪切应力u'v'分布的影响.研究结果表明...     

临界雷诺数下旋成体头部/后体和非对称涡流动响应间的确定性

 在尖拱形细长旋成体的大迎角（α=40°）流动中通过低速风洞测压实验研究了在临界雷诺数下模型头部扰动、后体粗糙度与非对称涡流动响应的确定性问题。实验雷诺数范围在1.0×10⁵～9.0×10⁵。实验结果分析表明，临界雷诺数下模型头部在不设置人工扰动情况下与非对称涡流动响应具有不确定性；而借鉴亚临界头部扰动与流动响应确定性问题的研究方法在模型头部设置人工扰动，结果显示响应存在确定性。关于后体粗糙度对响应的影响，实验结果表明临界雷诺数下该响应存在确定性。     

Low-frequency unsteadiness of vortex wakes over slender bodies at high angle of attack

A type of flow unsteadiness with low frequencies and large amplitude was investigated experimentally for vortex wakes around an ogive-tangent cylinder. The experiments were carried out at angles of attack of 60–80 and subcritical Reynolds numbers of 0.6–1.8×105. The reduced frequencies of the unsteadiness are between 0.038 and 0.072, much less than the frequency of Karman vortex shedding. The unsteady flow induces large fluctuations of sectional side forces. The results of pressure measurements and particle image velocimetry indicate that the flow unsteadiness comes from periodic oscillation of the vortex wakes over the slender body. The time-averaged vortex patterns over the slender body are asymmetric, whose orientation is dependent on azimuthal locations of tip perturbations. Therefore, the vortex oscillation is a type of unsteady oscillation around a time-averaged asymmetric vortex structure.     

Helium, Oxygen, Proton, and Electron (HOPE) Mass Spectrometer for the Radiation Belt Storm Probes Mission

The HOPE mass spectrometer of the Radiation Belt Storm Probes (RBSP) mission (renamed the Van Allen Probes) is designed to measure the in situ plasma ion and electron fluxes over 4π sr at each RBSP spacecraft within the terrestrial radiation belts. The scientific goal is to understand the underlying physical processes that govern the radiation belt structure and dynamics. Spectral measurements for both ions and electrons are acquired over 1 eV to 50 keV in 36 log-spaced steps at an energy resolution ΔE _FWHM/E≈15 %. The dominant ion species (H⁺, He⁺, and O⁺) of the magnetosphere are identified using foil-based time-of-flight (TOF) mass spectrometry with channel electron multiplier (CEM) detectors. Angular measurements are derived using five polar pixels coplanar with the spacecraft spin axis, and up to 16 azimuthal bins are acquired for each polar pixel over time as the spacecraft spins. Ion and electron measurements are acquired on alternate spacecraft spins. HOPE incorporates several new methods to minimize and monitor the background induced by penetrating particles in the harsh environment of the radiation belts. The absolute efficiencies of detection are continuously monitored, enabling precise, quantitative measurements of electron and ion fluxes and ion species abundances throughout the mission. We describe the engineering approaches for plasma measurements in the radiation belts and present summaries of HOPE measurement strategy and performance.     

机翼跨声速抖振数值模拟及模态分析

绕机翼的跨声速抖振流动是典型的复杂不稳定流动，对其非定常特性及失稳机制的研究具有重要的工程和学术价值。通过非定常雷诺平均Navier-Stokes（URANS）仿真方法和动模态分解（DMD）分析手段，研究了CRM（Common Research Model）等典型机翼的跨声速抖振流动特性及其主要失稳模态。数值仿真结果表明机翼的跨声速抖振表现为多失稳模式下的宽频特性。除了激波的弦向失稳，还会伴随发生激波的展向失稳，它们都表现为低频特性。翼梢处的高频响应可能是由激波诱导的低频失稳与翼尖涡相互耦合形成。DMD分析结果显示机翼展长和后掠因素诱导了激波展向失稳模态。本研究对抖振流动的物理建模、控制及理解相关的气动弹性现象具有指导意义。     

旋成体导弹小展弦比舵面大偏度对称状态下非对称流动机理

针对跨声速条件下,小展弦比截尖三角翼尾舵的旋成体导弹在小迎角、零侧滑、大舵偏对称状态下呈现出的非对称流动现象,本文首次对其进行了分析研究。首先,通过一系列测力试验、表面油流试验及粒子图像测速（PIV）试验对该非对称流动现象进行了精准捕捉,并对其产生的原因进行了分析。然后,基于已获得的试验数据及流场观测结果,借助数值模拟方法对所述非对称流动的细节、拓扑结构、空间形态及舵面压力分布等问题做了深入研究,并进行了详细讨论。结果表明：旋成体导弹小展弦比舵面大偏度对称偏转时,舵面前缘产生的翼尖涡会因舵面相距较近而相互干扰,促使翼尖涡沿流向非对称发展,使得舵面压力分布不均,最终导致非对称流动和较大横向量的产生,影响导弹的气动性能。