Advances in Aerodynamics

Abstract Large Eddy Simulations are carried out to analyze flow past flat plate in different configurations and inclinations. A thin flat plate is considered at three inclination angles (α = 30°, 60° and 90°) and three aspect ratios (AR = 0.5, 2 and 5). The Reynolds number based on the free stream velocity and chord length of the plate at different inclination angles varies between 75,000 to 150,000. An increase in the inclination angle while the aspect ratio (span to chord) is constant results in higher drag and lower lift on the plate. Increasing the aspect ratio at a constant inclination angle increases the mean aerodynamic loading except for the α = 30° and AR = 0.5 case where the mean forces are larger than the other aspect ratios for this specific inclination angle. The small aspect ratio suppresses and blocks the separation of the flow from the top and bottom edges causing larger aerodynamic forces relative to AR = 2, 5. Visualization of the flow structures shows the tip vortices have a significant role in controlling the shedding vortices from the top and bottom edges. At α = 30° and AR = 0.5, the two tip vortcies control and suppress the flow separation from the top and bottom edges. A stable wake was found for this case with no fluctuation. As the aspect ratio increases, the influence of the tip vortices on flow separation from the top and bottom edges reduces. As a result, larger fluctuations were found for cases with higher aspect ratios.

Mehrdad Shademan

Arash Naghib-Lahouti

Adv. Aerodyn.

Effects of aspect ratio and inclination angle on aerodynamic loads of a flat plate

平板纵横比和倾斜角对气动载荷的影响

Abstract For its outstanding aerodynamic capabilities, the integrated design of the waverider and inlet is widely accepted in hypersonic aircraft. Three aspects of the integrated design of the waverider and inlet since 2020 are mainly described in this paper. Firstly, the advantages and shortcomings of the conventional integrated design are examined. Then, different layouts of integrated design are proposed, and the aerodynamic performance optimization methods of the waverider, inlet, and their coupling are introduced. Besides, a series of methods for increasing the calculating accuracy of the waverider and inlet are presented, and the focus of attention is to consider the lateral flow problem.

Tianyu Gong

Yaosong Long

Zhongtao Cheng

Yiqing Li

Recent development of integrated design and improving methods of waverider and inlet

波阻板与进气道一体化设计及改进方法的最新进展

Abstract The accurate computation of different turbulent statistics poses different requirements on numerical methods. In this paper, we investigate the capabilities of two representative numerical schemes in predicting mean velocities, Reynolds stress and budget of turbulent kinetic energy (TKE) in low Mach number flows. With concerns on numerical order of accuracy, dissipation and dispersion properties, a high-order upwind scheme with relatively good dispersion and dissipation and a second-order non-dissipative central scheme with perfect dissipation but poor dispersion are adopted for this comparative study. By carrying out a series of numerical simulations including Taylor-Green vortex, turbulent channel flow at $$Re_{\tau }=180$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:mrow> <mml:mi>R</mml:mi> <mml:msub> <mml:mi>e</mml:mi> <mml:mi>τ</mml:mi> </mml:msub> <mml:mo>=</mml:mo> <mml:mn>180</mml:mn> </mml:mrow> </mml:math> and turbulent flow over periodic hill at $$Re_{b}=10595$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:mrow> <mml:mi>R</mml:mi> <mml:msub> <mml:mi>e</mml:mi> <mml:mi>b</mml:mi> </mml:msub> <mml:mo>=</mml:mo> <mml:mn>10595</mml:mn> </mml:mrow> </mml:math> , it can be obtained that although the high-order upwind scheme lacks perfection of dissipation in high wave number range, it still demonstrates superior predictive capability compared with the second-order non-dissipative central scheme, especially with relatively coarse grids. Finally, by taking the high-order upwind scheme as a suitable selection for turbulence simulation, the turbulent flow over a 30P30N multi-element airfoil is investigated as an application study. After briefly comparing the simulated profiles and spectrum with reference experimental results as validation, the budget of TKE is analyzed to locate the dominant flow structures and regions. It is found that the production and dissipation terms behave in a “monopole” pattern in the locations with strong shears and wakes. Whereas the advection and diffusion terms show an “inward” pattern and an “outward” pattern, which indicate the spatial transport of TKE between the center of the shear layer and nearby locations.

Dandi Wang

Yiming Du

Yao Jin

Jinsheng Cai

Fei Liao

Comparative study on predicting turbulent kinetic energy budget using high-order upwind scheme and non-dissipative central scheme

高阶迎风格式与无耗散中心格式预测湍流动能预算的比较研究

Abstract Advanced sensing techniques are in big demand for applications in hypersonic wind tunnel harsh environments, such as aero(thermo)dynamics measurements, thermal protection of aircraft structures, air-breathing propulsion, light-weighted and high-strength materials, etc. In comparison with traditional electromechanical or electronic sensors, the fiber optic sensors have relatively high potential to work in hypersonic wind tunnel, due to the capability of responding to a wide variety of parameters, high resolution, miniature size, high resistant to electromagnetic and radio frequency interferences, and multiplexing, and so on. This article has classified and summarized the research status and the representative achievement on the fiber optic sensing technologies, giving special attention to the summary of research status on the popular Fabry-Perot interferometric, fiber Bragg gratings and (quasi) distributed fiber optic sensors working in hypersonic wind tunnel environment, and discussed the current problems in special optical fiber sensing technologies. This article would be regarded as reference for the researchers in hypersonic wind tunnel experiment field.

Huacheng Qiu

Fu Min

Yanguang Yang

Fiber optic sensing technologies potentially applicable for hypersonic wind tunnel harsh environments

适用于高超声速风洞恶劣环境的潜在光纤传感技术

Abstract This study uses the Large Eddy Simulation (LES) technique to conduct an exhaustive analysis of the flow characteristics within the Rectangular-to-Elliptical shape Transition (REST) inlet under Mach 6 conditions. It mainly focuses on investigating the influence of the shock wave-turbulence interaction on the swirl distortion at the inlet exit. At the design condition, characterized by 0° Attack and 0° Sideslip, the incident shock wave at the inlet lip undergoes multiple reflections within the boundary layer of the domain wall, culminating in the formation of turbulent structures. The first reflected shock wave has the highest energy, exerting a significant impact on the boundary layer and the exit swirl distortion. On the contrary, the energy of the incident shock wave is progressively reduced due to repeated reflections, which results in reducing the exit swirl distortion. Under off-design conditions, characterized by 6° Attack and 0° Sideslip as well as 6° Attack with 6° Sideslip, variations in the incoming flow make the incident shock wave move inward, decreasing the frequency of shock wave reflections and even significantly reducing the reflected shock waves under conditions of 6° Attack and 6° Sideslip. However, this results in significantly increasing the exit swirl angle and distortion intensity. The obtained results demonstrate that changes in the incoming flow conditions significantly affect the level of exit swirl distortion by modulating the shock wave-turbulence interaction, especially in terms of the positioning of the incident shock wave and the quantity of reflected shock waves. In addition, this paper studies the wall heat transfer coefficient of the inlet. The obtained results show that the interaction between shock waves and the boundary layer significantly affects the heat transfer coefficient. This study provides a foundation for the comprehension and prediction of the performance of hypersonic inlets across a spectrum of flight conditions, and for the guidance of the design and optimization of such inlets.

Zhenlong Wu

Limei Lu

Xinyi Xu

Ranhui Liang

Influence of the shock wave-turbulence interaction on the swirl distortion in hypersonic inlet

激波-湍流相互作用对高超声速进气道旋流畸变的影响

Abstract The general synthetic iterative scheme (GSIS) has proven its efficacy in modeling rarefied gas dynamics, where the steady-state solutions are obtained after dozens of iterations of the Boltzmann equation, with minimal numerical dissipation even using large spatial cells. In this paper, the fast convergence and asymptotic-preserving properties of the GSIS are harnessed to remove the limitations of the direct simulation Monte Carlo (DSMC) method. The GSIS, which leverages high-order constitutive relations derived from DSMC, is applied intermittently, which not only rapidly steers the DSMC towards steady state, but also eliminates the requirement that the cell size must be smaller than the molecular mean free path. Several numerical tests have been conducted to validate the accuracy and efficiency of this hybrid GSIS-DSMC approach.

Liyan Luo

Lei Wu

Multiscale simulation of rarefied gas dynamics via direct intermittent GSIS-DSMC coupling

通过直接间断GSIS-DSMC耦合的多尺度稀薄气体动力学模拟

Abstract Steady-state numerical simulations were conducted to capture the aerodynamic characteristics and flow patterns resulting from a tubercled and non-tubercled wing subjected to various combined pitch and yaw conditions at $$Re=1.8 \times 10^{5}$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:mrow> <mml:mi>R</mml:mi> <mml:mi>e</mml:mi> <mml:mo>=</mml:mo> <mml:mn>1.8</mml:mn> <mml:mo>×</mml:mo> <mml:msup> <mml:mn>10</mml:mn> <mml:mn>5</mml:mn> </mml:msup> </mml:mrow> </mml:math> . Pitch angle ranged from $$0^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>0</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> to $$25^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>25</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> , while two different yaw angles of $$10^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>10</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> and $$30^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>30</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> were used. Results show that $$10^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>10</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> yaw angle does not impact upon the lift and drag characteristics significantly, while a $$30^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>30</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> yaw angle leads to substantial lift and drag losses. Additionally, the tubercled wing continues to confer favourable stall-mitigating characteristics even for the larger yaw angle. Finally, despite skewing the flow structures significantly, the $$30^{\circ }$$ <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML"> <mml:msup> <mml:mn>30</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:math> yaw angle also reduces the formations of bi-periodic flow structures, flow separations and recirculating regions along the leading-edge tubercles, suggesting potentially better flow stability and controllability.

T. H. New

S. Mandrà

On the effects of non-zero yaw on leading-edge tubercled wings

非零偏航角对前缘突起翼型影响的探讨

短名	Adv. Aerodyn.
Journal Impact	2.83
国际分区	PHYSICS, FLUIDS & PLASMAS(Q1)
期刊索引	中科院 3 区

ISSN	2524-6992
h-index	14
国内分区	工程技术(3区)工程技术工程机械(4区)工程技术力学(4区)工程技术物理流体与等离子体(4区)

涉及主题	物理热力学机械工程类数学航空航天工程计算机科学量子力学地理气象学几何学数学分析湍流材料科学经典力学空气动力学结构工程人工智能机械工程化学应用数学
出版信息	出版商: Springer China，出版周期: ，期刊类型: journal，开源期刊: 是
基本数据	创刊年份: 2019，原创研究文献占比: 84.21%，自引率:10.30%， Gold OA占比: 100.00%
平均审稿周期	网友分享经验：11 Weeks

Advances in Aerodynamics

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Effects of aspect ratio and inclination angle on aerodynamic loads of a flat plate

Recent development of integrated design and improving methods of waverider and inlet

Comparative study on predicting turbulent kinetic energy budget using high-order upwind scheme and non-dissipative central scheme

Fiber optic sensing technologies potentially applicable for hypersonic wind tunnel harsh environments

Influence of the shock wave-turbulence interaction on the swirl distortion in hypersonic inlet

Recent development of integrated design and improving methods of waverider and inlet

Comparative study on predicting turbulent kinetic energy budget using high-order upwind scheme and non-dissipative central scheme

Influence of the shock wave-turbulence interaction on the swirl distortion in hypersonic inlet

Multiscale simulation of rarefied gas dynamics via direct intermittent GSIS-DSMC coupling

On the effects of non-zero yaw on leading-edge tubercled wings