Entity

Time filter

Source Type


Zhang S.,CAS Institute of Mechanics | Yu X.,CAS Institute of Mechanics | Li F.,CAS Institute of Mechanics | Kang G.,Chinese Academy of Aerospace Aerodynamics | And 2 more authors.
Optics and Lasers in Engineering | Year: 2012

The quantitative local equivalence ratio measurements of premixed kerosene/air gas at elevated pressure by the laser induced breakdown spectroscopy (LIBS) technique were preformed in a high temperature test cell, which was designed and manufactured for simulated supersonic combustion state. According to in-situ experimental conditions in supersonic combustion, the correlations between the values of emission intensity ratio of H/O, H/N and the equivalence ratio of premixed kerosene/air mixture in different gas pressures was established. The dependence of the FWHM of H α on pressure of the mixture was also measured. Therefore, the laser diagnostic method for quantitative local equivalence ratio measurements of kerosene/air mixture by the LIBS technique in supersonic combustion was developed in laboratory. The fundamental data was prepared for on-line quantitative local equivalence ratio measurements of kerosene/air mixture in supersonic combustion experiments. © 2012 Elsevier Ltd. All rights reserved. Source


Hu X.Y.,TU Munich | Wang Q.,TU Munich | Wang Q.,Chinese Academy of Aerospace Aerodynamics | Adams N.A.,TU Munich
Journal of Computational Physics | Year: 2010

In this work, an adaptive central-upwind 6th-order weighted essentially non-oscillatory (WENO) scheme is developed. The scheme adapts between central and upwind schemes smoothly by a new weighting relation based on blending the smoothness indicators of the optimal higher order stencil and the lower order upwind stencils. The scheme achieves 6th-order accuracy in smooth regions of the solution by introducing a new reference smoothness indicator. A number of numerical examples suggest that the present scheme, while preserving the good shock-capturing properties of the classical WENO schemes, achieves very small numerical dissipation. © 2010 Elsevier Inc. Source


Tian J.-W.,Chinese Academy of Aerospace Aerodynamics | Yuan X.-J.,Chinese Academy of Aerospace Aerodynamics
Jisuan Lixue Xuebao/Chinese Journal of Computational Mechanics | Year: 2015

The 3rd order accurate Runge-Kutta discontinuous Galerkin (RKDG) method is developed to simulate three dimensional complex flows, such as three dimensional forward step problem, three dimensional Riemann problem and ball Riemann problem. Numerical results show that RKDG method can capture shocks and contact discontinuities in few grid points successfully. Furthermore, the pressure distribution of z=0.4 plane in ball Riemann problem agrees well with the result in the reference by refined grids. This suggested that the RKDG method developed in this paper is not only able to qualitatively describe three-dimensional complex flows, but also can be used in quantitative three-dimensional complex flow field calculations. ©, 2015, Editorial Office of Chinese Journal of Computational Mechanics. All right reserved. Source


Zhu Z.-B.,Chinese Academy of Aerospace Aerodynamics | Yuan X.-J.,Chinese Academy of Aerospace Aerodynamics | Chen L.,Chinese Academy of Aerospace Aerodynamics
Jisuan Lixue Xuebao/Chinese Journal of Computational Mechanics | Year: 2015

A high order parallel algorithm was developed for the simulation of supersonic complex multi-scale flows. The fifth-order upwind compact scheme based on finite volume method was utilized, and the characteristic limiter was used to prevent non-physical oscillations across discontinuity. The fifth WENO schemes were used in adjoining boundaries to achieve consistent precision order in the whole computing domain. Using zone decomposition method and message communicating interfaces, parallel calculation is carried out on MPI platform. The capability of the algorithm is demonstrated by solving supersonic test cases, and the parallel efficiency and speedup are analyzed. Then the algorithm is used for the simulation of supersonic transition and turbulence. The computed results reveal that the developed algorithm has the properties of high-order accuracy and high resolution. Besides, the computed flow fields are continuous in adjoining boundary, and the parallel computing efficiency is acceptable. The algorithm achieves admirable effect in the numerical simulation of supersonic turbulence. © 2015, Editorial Office of Chinese Journal of Computational Mechanics. All right reserved. Source


Ma Y.,Chinese Academy of Aerospace Aerodynamics | Liu X.-W.,Chinese Academy of Aerospace Aerodynamics | Ou P.,Chinese Academy of Aerospace Aerodynamics
Proceedings - 2015 7th International Conference on Intelligent Human-Machine Systems and Cybernetics, IHMSC 2015 | Year: 2015

Underwater glider is a new type of autonomous underwater vehicle driven by gravity. In order to study the relationship between the motion parameters and control variable of the underwater glider, solve the fluctuation problem of pitching angle and attack angle in the process of attitude changing, simulation via the software Mat lab is performed based on the kinematic equations of underwater glider in vertical plane. The results show that the longer the cycle of bary center adjusting, the smaller the fluctuating extent of the pitching angle. It seems that this fluctuation of underwater glider is not affected by the variation of buoyancy adjusting, and the fluctuation of attack angle may be affected by the time center location difference between these two adjusting cycles. © 2015 IEEE. Source

Discover hidden collaborations