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Gas kinetic flux solver based finite volume weighted essentially non-oscillatory scheme for inviscid compressible flows

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Applied Mathematics and Mechanics(English Edition) 2023年第6期44卷 961-980页

作者： Lan JIANG Jie WU Liming YANG Hao DONG State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Department of Aerodynamics Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

A high-order gas kinetic flux solver(GKFS)is presented for simulating inviscid compressible *** weighted essentially non-oscillatory(WENO)scheme on a uniform mesh in the finite volume formulation is combined with the circular function-based GKFS(C-GKFS)to capture more details of the flow fields with fewer *** from most of the current GKFSs,which are constructed based on the Maxwellian distribution function or its equivalent form,the C-GKFS simplifies the Maxwellian distribution function into the circular function,which ensures that the Euler or Navier-Stokes equations can be recovered *** improves the efficiency of the GKFS and reduces its complexity to facilitate the practical application of *** benchmark cases are simulated,and good agreement can be obtained in comparison with the references,which demonstrates that the high-order C-GKFS can achieve the desired accuracy.

关键词： circular function-based gas kinetic flux solver(C-GKFS) weighted essentially non-oscillatory(WENO)scheme compressible flow finite volume method

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CFD/CSD-based flutter prediction method for experimental models in a transonic wind tunnel with porous wall

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Chinese Journal of Aeronautics 2020年第12期33卷 3100-3111页

作者： Tongqing GUO Daixiao LU Zhiliang LU Di ZHOU Binbin LYU Jiangpeng WU Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China China Aerodynamics Research and Development Center Mianyang 621000China Shenyang Aircraft Design and Research Institute Shenyang 110035China

To predict the flutter dynamic pressure of a wind tunnel model before flutter test,an accurate Computational Fluid Dynamics/Computational Structural Dynamics(CFD/CSD)-based flutter prediction method is proposed under the conditions of a 2.4 m×2.4 m transonic wind tunnel with porous *** the CFD simulations of the flows through an inclined hole of this wind tunnel,the Nambu's linear porous wall model between the flow rate and the differential pressure is extended to the porous wall with inclined holes,so that the porous wall can be conveniently modeled as a boundary *** to the flutter testing approach for the current wind tunnel,the steady CFD calculation is conducted to achieve the required inlet Mach number.A timedomain CFD/CSD method is then employed to evaluate the structural response of the experimental model,and the critical flutter point is obtained by increasing the dynamic pressure step by step at a fixed Mach *** present method is applied to the flutter calculations for a vertical tail model and an aircraft model tested in the current transonic wind *** both models,the computed flutter characteristics agree well with the experimental results.

关键词： CFD/CSD Experimental models Flutter Porous wall Transonic wind tunnel

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Evolution of wall flow structure and measurement of shear stress issuing from supersonic jet with extended shelf

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Chinese Journal of Aeronautics 2021年第11期34卷 94-105页

作者： Yun JIAO Chengpeng WANG Jiaqi XIE Kang LI Kerning CHENG College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

This paper reports an experimental study on the supersonic jet surface flow structure visualization and shear stress field measurement issuing from a rectangular nozzle with extended shelf. The evolution of the near-field surface flow structures with an increased Nozzle Pressure Ratio(NPR) is successfully captured by the surface oil flow, infrared detection technology, and the Shear-Sensitive Liquid Crystal Coating(SSLCC) technique. Results reveal that under smaller NPR, the wall flow structure is similar to that of a jet without the extended shelf i.e., clean jets,and this is caused by insufficient effect on the boundary layer. However, at higher amplitudes of NPR, there exists a significant effect of the boundary layer, as a near triangular separation forms on the trailing edge of the Mach stem due to the adverse pressure gradient, which is visualized for the very first time in this paper. Furthermore, the vector field of shear stress is measured quantitatively by SSLCC technique. Results shows that the magnitude of shear stress heightened with NPR increasing, and the directions of shear stress changes across the shock wave and expansion fans. In addition, surface streamlines measured by SSLCC is significantly consistent with the streamlines visualized using the oil flow technique.

关键词： Evolution of shock structure flow visualization Quantitative measurement Shear stress Supersonic jet

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A Novel Quantum Fourier Ordinary Differential Equation Solver for Solving Linear and Nonlinear Partial Differential Equations

arXiv

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arXiv 2025年

作者： Xiao, Y. Yang, L.M. Shu, C. Du, Y.J. Song, Y.X. Department of Aerodynamics College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Nanjing210016 China State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics Nanjing210016 China MIIT Key Laboratory of Unsteady Aerodynamics and Flow Control Nanjing University of Aeronautics and Astronautics Nanjing210016 China Department of Mechanical Engineering National University of Singapore Singapore117576 Singapore

In this work, a novel quantum Fourier ordinary differential equation (ODE) solver is proposed to solve both linear and nonlinear partial differential equations (PDEs). Traditional quantum ODE solvers transform a PDE into an ODE system via spatial discretization and then integrate it, thereby converting the task of solving the PDE into computing the integral for the driving function f(x). These solvers rely on the quantum amplitude estimation algorithm, which requires the driving function f(x) to be within the range of [0, 1] and necessitates the construction of a quantum circuit for the oracle that encodes f(x). This construction can be highly complex, even for simple functions like f(x) = x. An important exception arises for the specific case of f(x) = sin2(mx+c), which can be encoded more efficiently using a set of Ry rotation gates. To address these challenges, we expand the driving function f(x) as a Fourier series and propose the Quantum Fourier ODE Solver. This approach not only simplifies the construction of the oracle but also removes the restriction that f(x) must lie within [0,1]. The proposed method was evaluated by solving several representative linear and nonlinear PDEs, including the Navier-Stokes (N-S) equations. The results show that the quantum Fourier ODE solver produces results that closely match both analytical and reference solutions. Copyright © 2025, The Authors. All rights reserved.

关键词： Navier Stokes equations

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On the investigation of shock wave/ boundary layer interaction with a high‑order scheme based on lattice Boltzmann flux solver

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Advances in aerodynamics 2024年第1期6卷 486-506页

作者： Jian Qin Haichuan Yu Jie Wu State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyDepartment of AerodynamicsNanjing University of Aeronautics and AstronauticsNanjing 210016China China Academy of Launch Vehicle Technology Beijing 100076China

Shock wave/boundary layer interaction(SWBLI)continues to pose a significant chal-lenge in the field of aerospace *** paper aims to address this issue by proposing a novel approach for predicting aerodynamic coefficients and heat trans-fer in viscous supersonic and hypersonic flows using a high-order flux reconstruction ***,finite volume methods are extensively employed for the compu-tation of skin aerodynamic coefficients and heat ***,these numerical methods exhibit considerable susceptibility to a range of factors,including the inviscid flux function and the computational *** application of high-order flux recon-struction techniques offers promising potential in alleviating these *** contrast to other high-order methods,the flux reconstruction is combined with the lat-tice Boltzmann flux solver in this *** current method evaluates the common inviscid flux at the cell interface by locally reconstructing the lattice Boltzmann equa-tion solution from macroscopic flow variables at solution ***,this framework performs a positivity-preserving,entropy-based adaptive filtering method for shock *** present approach is validated by simulating the double Mach reflection,and then simulating some typical viscous *** results demonstrate that the current method accurately predicts aerodynamic coefficients and heat trans-fer,providing valuable insights into the application of high-order methods for shock wave/boundary layer interaction.

关键词： Shock wave/boundary layer interaction High order method Flux reconstruction Lattice Boltzmann flux solver Entropy-based adaptive filtering method

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An integration method based on a novel combined flow for aerodynamic configuration of strutjet engine

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Chinese Journal of Aeronautics 2021年第9期34卷 156-167页

作者： Longsheng XUE Chuan CHENG Chengpeng WANG Keming CHENG College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China Aerospace System Engineering Shanghai Shanghai 201100China

In this paper a novel design method of aerodynamic configuration is proposed to integrate forebody,strut and inlet for strutjet engine,and a model at design point of Mach number6 is generated to investigate the aerodynamic performance by both simulations and *** basic flow field employed by proposed method is a combined flow named IBB,which is combined by Internal Conical flow A(ICFA),truncated Busemann flow I(BI)for external section,and truncated Busemann flow II(BII)for internal *** model configuration is generated by streamline tracing method from basic flow field,in which the forebody section is traced from ICFA and BI flows,and the inlet as well as strut section is traced from BII *** simulations in Mach number 4,5,and 6 demonstrate uniform starting flow fields with relatively high total pressure recovery,which agree well with experiments in wind ***,in low Mach number cases,this inlet could start at Mach number 3 while it is unstarted at Mach number 2.7;in high Mach number cases,a uniform flow could still exist in Mach number 6.5 while a relatively strong shock wave boundary layer interaction is found in cowl area of Mach number 7 case,indicating the inlet designed by proposed method works in a relatively wide Mach number range.

关键词： Airframe-propulsion integration Busemann flow Combined flow Hypersonics Wind tunnel test

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Oblique shock train motion based on schlieren image processing

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Chinese Journal of Aeronautics 2023年第3期36卷 30-41页

作者： Longsheng XUE Chuan CHENG Chengpeng WANG Lantian ZHANG Kang LI Keming CHENG College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China Beijing Institute of Tracking and Telecommunication Technology Beijing 100094China Aerospace System Engineering Shanghai Shanghai 201109China

In this paper,shock train motion in a Mach number 2.7 duct is studied experimentally,and large numbers of schlieren images are obtained by a high-speed *** image processing method based on Maximum Correlation Detection(MCD)is proposed to detect shock train motion from the schlieren images,based on which the key structures,e.g.,separation positions and separation shock angles on the top and bottom walls,can be analysed in *** oscillations of the shock train are generated by rhombus and ellipse shafts at various excitation *** to the analysis of MCD results,the distributions of the frequency components of shock train oscillation generated by the two shafts are distinctly different,in which the motion generated by the ellipse shaft is much smoother;shock train motion is mainly characterized by the oscillation of separation position while the separation shock strength is not so sensitive to downstream disturbance;there is a hysteresis loop relation between the downstream pressure and separation position.

关键词： Frequency components Hysteresis loop Maximum Correlation Detection(MCD) Schlieren image processing Shock train oscillation

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Study on Opposing Jet Simulation of Near Space Supersonic Vehicle Based on DSMC Method 19

Study on Opposing Jet Simulation of Near Space Supersonic Ve...

引用

19th International Bhurban Conference on Applied Sciences and Technology, IBCAST 2022

作者： Shen, Yi Xu, Xiao Zhang, Jun Zhang, Zhaoming Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information Technology Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing China School of Mechatronics and Power Engineering Jiangsu Zhenjiang China

ISBN: (数字)9781665460514

ISBN: (纸本)9781665460514

There are serious aerodynamic heating and high resistance phenomena for near space supersonic aircraft. Application of opposing jet flow is an effective technology for drag and heat reduction. This paper uses DSMC method to simulate the external opposite flow of aircraft moving in the supersonic flow in rarefied environment of near space. It analyzes the advantages and disadvantages of drag and heat reduction of opposing jet in the different conditoins by adjusting speeds of the jet in order to obtain an optimized scheme. The numerical results show that the peak values of aircraft surface pressure, surface heat flux and friction are reduced by 76.6%, 93.5% and 50.0% respectively. Application of opposing jet in rarefied environment can effectively reduce the drag and aerodynamic heating for supersonic aircraft. The present study provides an effective reference for the aircraft design on the drag and heat reduction. © 2022 IEEE.

关键词： Supersonic aircraft

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A sharp-interface immersed boundary method for simulating high-speed compressible inviscid flows

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Advances in aerodynamics 2020年第1期2卷 455-473页

作者： Junjie Wang Xiangyu Gu Jie Wu Department of Aerodynamics Nanjing University of Aeronautics and AstronauticsNanjing 210016China China Academy of Launch Vehicle Technology Beijing 100076China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

This paper presents a robust sharp-interface immersed boundary method for simulating inviscid compressible flows over stationary and moving *** flow field is governed by Euler equations,which are solved by using the open source library *** such as those introduced by shock waves are captured by using Kurganov and Tadmor divergence ***-slip boundary conditions are enforced at the boundary of body through reconstructing flow variables at some ghost *** values are obtained indirectly by interpolating from their mirror points.A bilinear interpolation is employed to determine the variables at the mirror points from boundary conditions and flow conditions around the *** validate the efficiency and accuracy of this method for simulation of high-speed inviscid compressible flows,four cases have been simulated as follows:supersonic flow over a 15°angle wedge,transonic flow past a stationary airfoil,a piston moving with supersonic velocity in a shock tube and a rigid circular cylinder lift-off from a flat surface triggered by a shock *** to the exact analytical solutions or the results in literature,good agreement can be achieved.

关键词： Immersed boundary method Inviscid compressible flows Sharp interface Shock waves OpenFOAM

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Influence of Ship Motion on flow Field over Modified Simple Frigate Shapes

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Transactions of Nanjing University of Aeronautics and Astronautics 2021年第3期38卷 520-534页

作者： LI Tong WANG Yibin ZHAO Ning Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

When the frigate moves forward,due to the ship motion such as pitching and rolling,the flow over the flight deck becomes very complex,which may seriously threaten the taking off and landing of the ship-borne *** flow fields over the different modified simple frigate shape(SFS)models,consisting of the hangar and flight deck,were numerically studied by changing the ratio of hangar height and length in the static state and pitching *** different models,the contours of velocity and pressure above the flight deck,as well as the variations of velocity components of the observation points and line in static state and pitching state were compared and *** results show that the size of recirculation zone and the location of the reattachment point have distinct differences for diverse models,and reveal the tracks of recirculation zone’s center and reattachment position in a pitching *** addition,the velocity components at two observation positions also change periodically with the periodic ***,the deviations of the velocity components in static state and pitching state are relatively large,therefore,the flow fields in static state cannot be used to simulate that in pitching state correctly.

关键词： computational fluid dynamics simple frigate shape ship airwake pitching recirculation zone

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