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高超声速飞行器激波位置的准确预测能够有效提升数值模拟的精度和效率。一方面,对高超声速飞行器激波附近网格进行正交和加密处理,可有效提升数值计算精度;另一方面,使用高超声速飞行器激波位置对计算网格进行修正,能够加速CFD计算收敛过程。提出了一种基于机器学习的高超声速飞行器激波智能预测方法,对典型高超声速飞行器外形进行激波位置的高效准确预测。首先,针对典型高超声速飞行器外形和典型飞行状态,使用数值模拟方法获得收敛的流场,并采用基于Mach数等值线的激波提取方法,从流场中判别激波面并提取构成激波面的关键点位置,形成训练数据;然后采用有监督学习算法,学习关键点位置,并利用二次曲线沿流向拟合关键点形成初步的激波线族;最后,基于剖面压力云图,构造基于投影压力图像的智能预测神经网络,对初步形成的激波线族进行修正,并获得三维激波面。大量的实验结果表明,激波预测模型能够对高超声速飞行器激波位置做出准确预测,预测的激波面与CFD数值计算结果中提取的激波面误差在10-4量级。 相似文献
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通过数值模拟研究了高超声速来流绕过压缩拐角的层流分离三维流动特性.数值方法采用三维N-S方程,结合2阶精度Roe格式以及分区结构网格有限体积法进行离散.数值模拟的空间激波结构与实验纹影结果符合较好;激波/边界层干扰区内3条纵向线上的计算压力分布与实验结果进行了对比分析,计算获得在三维楔侧面存在低压力区,与实验结果反映的规律一致,计算结果表明低压力区是由楔体侧缘尖端发起的二次涡的抽吸作用造成的.此外,在楔体后端尾流区的低压沿边界层内的亚声速区往上游传递了一定距离. 相似文献
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TVD格式是目前数值研究以激波为主要特征之一的超声速、高超声速流场的最先进的算法之一。本文用二阶迎风TVD格式,对三种烧蚀外形的轴对称粘性流场和10°钝锥有攻角三维粘性流场进行了数值模拟,得到了高质量的头部脱体激波和与实验结果及直线推进法计算一致的物面压力分布,表明了TVD格式在再入体粘性绕流计算中的独特优势。 相似文献
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使用计算流体动力学的方法,对经典的运动激波绕射现象做数值模拟,研究了一类复杂激波反射问题一入射的运动斜激波绕射现象.给出一组运动斜激波绕射波纹壁面的非定常过程的模拟结果。计算结果显示出由运动斜激波绕射诱导的多波干扰产生的复杂流场结构。 相似文献
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The presence of an adverse pressure gradient, shock/shock interaction and shock wave/boundary layer interaction often induces
flow separation around bodies. However, the effect of dissociated flow on separated flow characteristics, especially at hypersonic
speeds, is still not clear, and considerable differences are observed between experiments and numerical simulations. In this
investigation, the unsteady separated flow features around double cones are visualized in the Shock Wave Research Center (SWRC)
free-piston driven shock tunnel at a nominal Mach Number of 6.99 using multiple optical techniques. The time resolved shock
structure oscillations in the flow field around double cones (first cone, semi-apex angle = 25°; second cone, semi-apex angles=50°,
65°, 68° and 70°) have been visualized using a high-speed image converter camera (IMACON) at a nominal stagnation enthalpy
of 4.8 MJ/kg. In addition, flow visualization studies around the double cone is also carried out using Schlieren and double
exposure holographic interferometry in order to precisely locate the separation point and measure the separation length. The
presence of a triple shock structure in front of the second cone and a non-linear unsteady shock structure oscillation in
the flow field are the significant results from visualization studies on the 25° /65°, 25° /68° and 25°/70° double cones.
On the other hand, the flow field around 25° /50° is relatively steady and Type V shock/shock interaction is observed. Illustrative
numerical simulation studies are carried out by solving N-S equations to complement the experiments. The simulated flow features
around a double cone agree well qualitatively with experiments. 相似文献
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研究了局域能量脉冲注入条件下高超声速进气道流场的扰动情况。数值模拟采用三维雷诺平均N-S方程,分别利用ROE格式和二阶中心格式对对流通量和粘性通量进行离散处理;用高斯-赛德尔隐式格式对方程进行时间推进求解,采用k-ε两方程模型用于湍流的数值模拟。开展了高超风洞平板流场能量注入实验,获取了高速纹影图像,并对实验结果与计算结果进行比较。研究表明,能量注入产生的冲击波能与高超流动产生的斜激波发生强烈干扰,脉冲能量的引入可能引起高超声速进气道流量俘获率产生剧烈震荡,从而导致进气道流场的性能急剧下降。 相似文献
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F. Grisch P. Bouchardy M. Péalat B. Chanetz T. Pot M. C. Coët 《Applied physics. B, Lasers and optics》1993,56(1):14-20
Rotational temperature and nitrogen number density are measured in the shock wave/boundary layer interaction region in the vicinity of a two-dimensional compression corner disposed in a low pressure, 55 K, Mach 10 hypersonic air flow. Spatially-resolved data are recorded using a nonlinear optical technique named dual-line coherent anti-Stokes Raman scattering (DLCARS). Averaged temperature and density profiles are compared with those predicted by a Navier-Stokes solver. Good agreement is found. 相似文献
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The impact of flow induced loads on snap-through behavior of acoustically excited, thermally buckled panels 总被引:1,自引:0,他引:1
The analysis, and ultimately the design, of air-breathing hypersonic cruise-type vehicles is hampered by the inability to accurately capture the coupled fluid-thermal-structure interactions. There are few laboratory experiments that have investigated the interactions of compliant surface panels and hypersonic flow. The vast majority of experimental studies are limited to replicating only parts of the physical mechanisms and couplings because of the difficulty in imposing the complete transient, hypersonic environment. Studies of hot-structures, thermal protection systems, or exotic material and structural configurations, typically neglect vibration induced fluctuating pressures, shock-boundary layer interaction, the effect of transition, and separated flow. Conversely, hypersonic wind-tunnel experiments purposely neglect the influence of non-rigid structure on the aforementioned high-speed flow effects in an effort to better understand the nature of the high-speed effects. The goal of this study is to implement a simple computational model that seeks to incorporate many of the fluid-thermal-structure interactions inherent in hypersonic flow. This is accomplished using simplified aerothermal and aerodynamic theories in conjunction with a simply supported von Kármán panel in cylindrical bending. Comparisons are made between the inclusion and exclusion of self-induced and forced fluctuating pressures, as well as the fidelity required in computing the temperature distributions. Results indicate that self-induced pressure fluctuations, which arise from interactions of a vibrating structure with an ambient mean flow, significantly impact the response of panels to random acoustic loadings. Additionally, the inclusion of forced fluctuating pressure loadings can significantly reduce the onset time of panel flutter. It is surmised that experimental investigations must combine thermal loads, as well as both forced and self-induced fluctuating pressures. 相似文献
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为进行高超声速气动热数据相关性研究, 选取了一平板-锥组合体模型为研究对象, 开展不同缩比模型的风洞试验, 分别使用3种不同方法进行气动热试验数据的相关性研究.研究结果表明, 使用正激波后Reynolds数Rens和修正的黏性干扰系数V*/Sw可以将不同缩比模型不同来流条件下的Stanton数进行较好的关联, Stanton数与正激波后Reynolds数Rens成反比例关系, 与修正的黏性干扰系数V*/Sw成正比例关系.最后基于相关性研究结论和理论分析, 提出了一种模型表面传热现象的数学模型. 相似文献
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A two-dimensional simulation model is used to study the gasdynamic structure of a rarefied hypersonic flow of molecular nitrogen in a curvilinear channel in which the lower surface carries the cathode section of the discharge gap whereas the upper surface serves as the anode. The electrodynamic structure of the glow discharge (the distribution of concentrations of charged species, current density, and electric potential) is examined. It was demonstrated that the burning of a glow discharge in a rarefied hypersonic flow makes it possible to effectively modify the shock wave structure of the flow. 相似文献
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The article presents research on a wet steam transonic flow in a Laval half-nozzle with a shock wave. The motivation for this research was to investigate the shock wave/liquid phase interaction in the transonic wet steam flow. This phenomenon is responsible for the lack of good correspondence between experimental data and computational fluid dynamics results. For the tests, the geometry of the half-arc nozzle was used. The shock wave formation at the divergent section of the nozzle is caused by too high back-pressure. The observed instabilities in the flow are mainly initiated by the shock wave/liquid film (boundary layer) interaction. The numerical calculations were compared with experimental results with respect to the static pressure distribution along the nozzle. 相似文献
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利用三维并行计算代码求解Navier-Stokes方程,数值模拟标模(ELECTRE)化学非平衡绕流,研究真实气体效应对标模气动热特性的影响,反应模型为Dunn和Kang的7组元7反应化学动力学模型.利用典型弹道点的飞行试验数据验证化学非平衡流计算程序的可靠性.在此基础上,研究不同壁面催化条件下攻角和高度变化对热流的影响.计算表明:真实气体效应主要发生在物面附近很薄的激波层内,并使激波脱体距离减小;完全催化壁驻点热流值高于非催化壁热流值;随着攻角增大,热流分布差异明显,而且攻角越大时,物面电子数密度越小;飞行高度越高,O2和N2离解程度越低,驻点热流越低. 相似文献
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Abstract
This paper describes experimental and numerical investigations into the multiple shock waves/turbulent boundary layer interaction in a supersonic inlet. The test model has a rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain the visualization images and static pressure data by using supersonic wind tunnel. Numerical simulation was performed by solving the RANS equations with the Menter’s SST turbulent model. The inflow condition was a free-stream Mach number of 2.5 and a unit Reynolds number of 7.6 × 107/m. Numerical results showed good agreement with the experimental results. Based on this agreement, the flow characteristics which are often very difficult to obtain experimentally alone were analyzed with the aid of numerical simulation. The structures, pressure and velocity distributions, and total pressure loss of the pseudo-shock wave in the supersonic inlet were presented in detail from flow visualization images and static pressures. 相似文献20.
针对爆轰波在炸药-金属界面上折射时由实验获得的金属折射冲击波压力与经典爆轰波极曲线理论预测的压力存在显著差异这一问题, 本文展开了进一步的理论和数值模拟分析研究. 首先通过分析指出经典爆轰波极曲线理论的缺陷, 并对爆轰波极曲线理论进行了改进, 改进爆轰波极曲线理论给出了炸药爆轰波折射类型以及折射冲击作用点处的压力值. 然后发展了一个基于次特征理论来数值求解爆轰反应流动控制方程的二阶中心型Lagrange方法, 并数值模拟了一个典型的炸药爆轰波折射实验. 改进爆轰波极曲线理论和数值模拟分析结果表明, 爆轰波折射类型有三种:反射冲击波的正规折射、带Mach反射的非正规折射、无反射波的正规折射, 并且金属折射冲击波压力值随入射角增大而单调减小. 相似文献