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| 1 | Initial virtual flight test for a dynamically similar aircraft model with control augmentation system显示文摘To satisfy the validation requirements of flight control law for advanced aircraft,a wind tunnel based virtual flight testing has been implemented in a low speed wind tunnel.A 3-degree-offreedom gimbal,ventrally installed in the model,was used in conjunction with an actively controlled dynamically similar model of aircraft,which was equipped with the inertial measurement unit,attitude and heading reference system,embedded computer and servo-actuators.The model,which could be rotated around its center of gravity freely by the aerodynamic moments,together with the flow field,operator and real time control system made up the closed-loop testing circuit.The model is statically unstable in longitudinal direction,and it can fly stably in wind tunnel with the function of control augmentation of the flight control laws.The experimental results indicate that the model responds well to the operator's instructions.The response of the model in the tests shows reasonable agreement with the simulation results.The difference of response of angle of attack is less than 0.5°.The effect of stability augmentation and attitude control law was validated in the test,meanwhile the feasibility of virtual flight test technique treated as preliminary evaluation tool for advanced flight vehicle configuration research was also verified. | Guo Linliang Zhu Minghong Nie Bowen Kong Peng Zhong Chengwen | 2017 | Chinese Journal of Aeronautics2017，30，2： | 12 |
| 2 | Large-eddy simulation of wall-bounded turbulent flow with high-order discrete unified gas-kinetic scheme显示文摘In this paper,we introduce the discrete Maxwellian equilibrium distribution function for incompressible flow and force term into the two-stage third-order Discrete Unified Gas-Kinetic Scheme(DUGKS)for simulating low-speed turbulent flows.The Wall-Adapting Local Eddy-viscosity(WALE)and Vreman sub-grid models for Large-Eddy Simulations(LES)of turbulent flows are coupled within the present framework.Meanwhile,the implicit LES are also presented to verify the effect of LES models.A parallel implementation strategy for the present framework is developed,and three canonical wall-bounded turbulent flow cases are investigated,including the fully developed turbulent channel flow at a friction Reynolds number(Re)about 180,the turbulent plane Couette flow at a friction Re number about 93 and lid-driven cubical cavity flow at a Re number of 12000.The turbulence statistics,including mean velocity,the r.m.s.fluctuations velocity,Reynolds stress,etc.are computed by the present approach.Their predictions match precisely with each other,and they are both in reasonable agreement with the benchmark data of DNS.Especially,the predicted flow physics of three-dimensional lid-driven cavity flow are consistent with the description from abundant literature.The present numerical results verify that the present two-stage third-order DUGKS-based LES method is capable for simulating inhomogeneous wall-bounded turbulent flows and getting reliable results with relatively coarse grids. | Rui Zhang Chengwen Zhong Sha Liu Congshan Zhuo | 2020 | Advances in Aerodynamics2020，2，1： | 1 |
| 3 | Physical Body Impact After High Altitude Bail-out显示文摘In most of the emergency circumstances,the aircrew leaves the aircraft under unsatisfied conditions,such as too high relative velocity to the ambient air or low partial oxygen pressure.The aircrew must pass through this area as quickly as possible before opening the parachute safely,viz.,free-fall.Numerical simulations are conducted in this paper to explore the major characteris-tics of the aircrew free-fall process by using a commercial computational fluid dynamic(CFD) software,FLUENT.Coupled with the classical pressure-altitude and temperature-altitude relations,Navier-Stokes(N-S) equations for compressible flow are solved by using finite volume method.The body velocity and the attitude are predicted with six-degree of freedom(6DOF) module.The evolution of velocities,including horizontal,vertical components and angular velocity,is obtained.It is also analyzed further according to the particle kinetic theories.It is validated that the theories can predict the process qualitatively well with a modi-fied drag effect,which mainly stems from the velocity pressure.An empirical modification factor is proposed according to the fitting results. | CHEN Xiaopeng GUAN Huanwen ZHUO Congshan FENG Wenchun ZHONG Chengwen | 2011 | Chinese Journal of Aeronautics2011，24，2： | 1 |
| 4 | An Immersed-Boundary Method Based on the Gas Kinetic BGK Scheme for Incompressible Viscous Flow 显示文摘 | YUAN Ruifeng ZHONG Chengwen ZHANG He | 2015 | Journal of Computational Physics2015，296，： | 1 |
| 5 | Application of Lattice Boltzmann Method to Simulation of Compressible Turbulent Flow显示文摘The main goal of this paper is to develop the coupled double-distributionfunction(DDF)lattice Boltzmann method(LBM)for simulation of subsonic and transonic turbulent flows.In the present study,we adopt the second-order implicit-explicit(IMEX)Runge-Kutta schemes for time discretization and the Non-Oscillatory and NonFree-Parameters Dissipative(NND)finite difference scheme for space discretization.The Sutherland’s law is used for expressing the viscosity of the fluid due to considerable temperature change.Also,the Spalart-Allmaras(SA)turbulence model is incorporated in order for the turbulent flow effect to be pronounced.Numerical experiments are performed on different turbulent compressible flows around a NACA0012 airfoil with body-fitted grid.Our numerical results are found to be in good agreement with experiment data and/or other numerical solutions,demonstrating the applicability of the method presented in this study to simulations of both subsonic and transonic turbulent flows. | Congshan Zhuo Chengwen Zhong Kai Li Shengwei Xiong Xiaopeng Chen Jun Cao | 2010 | Communications in Computational Physics2010，8，10： | 0 |
| 6 | Pseudopotential-based discrete unified gas kinetic scheme for modeling multiphase fluid flows显示文摘To directly incorporate the intermolecular interaction effects into the discrete unified gas-kinetic scheme(DUGKS)for simulations of multiphase fluid flow,we developed a pseudopotential-based DUGKS by coupling the pseudopotential model that mimics the intermolecular interaction into DUGKS.Due to the flux reconstruction procedure,additional terms that break the isotropic requirements of the pseudopotential model will be introduced.To eliminate the influences of nonisotropic terms,the expression of equilibrium distribution functions is reformulated in a moment-based form.With the isotropy-preserving parameter appropriately tuned,the nonisotropic effects can be properly canceled out.The fundamental capabilities are validated by the flat interface test and the quiescent droplet test.It has been proved that the proposed pseudopotential-based DUGKS managed to produce and maintain isotropic interfaces.The isotropy-preserving property of pseudopotential-based DUGKS in transient conditions is further confirmed by the spinodal decomposition.Stability superiority of the pseudopotential-based DUGKS over the lattice Boltzmann method is also demonstrated by predicting the coexistence densities complying with the van der Waals equation of state.By directly incorporating the intermolecular interactions,the pseudopotential-based DUGKS offers a mesoscopic perspective of understanding multiphase behaviors,which could help gain fresh insights into multiphase fluid flow. | Zeren Yang Sha Liu Congshan Zhuo Chengwen Zhong | 2022 | Advances in Aerodynamics2022，4，1： | 0 |
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