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2012 Vol. 38, No. 7

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Flow separation control on control surface by blowing from leading edge of control surface
Deng Xueying, Wu Peng, Wang Yankui
2012, (7): 853-856.
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Abstract:
The wind tunnel experimental research on the flow separation control of control surface by blowing from leading edge of control was performed in D4 wind tunnel at Beihang University, in order to reduce the blowing air consumption. Blowing position was set at the separation point. The evolvement cour...
Attachment saddle point topology and transformation of 3-D separation in juncture flow
Zhang Hua, Hu Bo, Muhammad Yamin Younis, Wang Hong
2012, (7): 857-861.
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Abstract:
An experimental investigation of laminar boundary layer 3-D steady separation vortex flow upstream of junctures had been conducted to verify the existence of attachment saddle point topology and to study the transformation of the flow topology. The laser light sheet of 2-D particle image velocimetry...
Investigation on non-linear characteristic of pitching moment of joined wing configuration aircraft
Wang Yankui, Shan Jixiang, Tian Wei, Deng Xueying
2012, (7): 862-866.
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Abstract:
The joined wing configuration is one of the best configurations for the next transonic aircraft due to the advantage in the drag and lift characteristic, but the pitching moment changes non-linearly with the attack angle increasing in some condition. To solve the problem, the investigations of flow ...
Trim induced drag analysis and optimization of elastic twin-tailboom aircraft
Wang Libo, Yang Chao, Wu Zhigang
2012, (7): 867-872.
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Based on the energy method, the trim equations of flexible aircraft considering static aeroelasticity are derived. The idea of using static vortex lattice method combined with Trefftz plane theory and empirical formula to solve the induced drag and trim drag of flexible aircraft in trimmed level fli...
Vortex interaction mechanism over close-coupled canard configuration
Liu Peiqing, Wang Yaping, Liu Jie, Qu Qiulin
2012, (7): 873-876,881.
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Numerical investigation on the vortical structure was carried out on a simplified close-coupled canard configuration with a 50° swept delta wing and a 50° swept delta canard at various angle of attack (AOA) by solving Reynolds averaged Navier-Stokes(N-S) equations at 2.4×105 Reynolds number. The vor...
Hypersonic boundary layer transition prediction based on laminar fluctuation energy transport equation
Song Bo, Lee Chunhian
2012, (7): 877-881.
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Abstract:
The transition of boundary layer flows has crucial effects on aerodynamic and heat performances of hypersonic vehicles. The fluctuation energy transport equation based on Favr average was solved in conjunction with the Favr averaged Navier-Stokes equations to predict the onset of the boundary layer ...
Characteristics of temperature oscillation inthermocapillary convection in rectangular pool
Zhu Peng, Duan Li, Kang Qi
2012, (7): 882-885.
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Experimental and numerical results on characteristics of temperature oscillation in a rectangular pool of silicone oil were presented. A thermocapillary-convection controlling system was established in laboratory to study the critical condition and characteristics of temperature oscillation. The app...
Numerical investigation on separation control for flow over a bump with synthetic jet
Chen Zhanjun, Ba Yulong, Wang Jinjun
2012, (7): 886-890.
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Numerical simulation on the separation flow control over a bump was carried out with synthetic jet actuator before the separation point. The Reynolds averaged Navier-Stocks equations were solved by FLUENT® 6.3. The mechanism of synthetic jet actuator flow separation control was discussed by analyzin...
Nature of vortex bifurcation and cascade in isotropic turbulence
Ran Zheng
2012, (7): 891-894,952.
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Abstract:
The central problem of fully developed turbulence is understanding the energy cascading process and multiscale interaction. Update, there is no deductive theory which leads to a full physical understanding or mathematical formulation. The definition, development,challenge and the corresponding statu...
Numerical simulation of a new-style 2D thrust vectoring nozzle
Xiao Zhongyun, Jiang Xiong, Chen Zuobin, Liu Gang
2012, (7): 895-899.
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To exclude the inefficiency of existing fluidic thrust vectoring techniques, a new-style nozzle using ejecting mixing effects was proposed, which produced thrust vectoring by making use of the tendency of a fluid jet to be attracted to a nearby surface. The vectoring angles were manually controlled ...
Two-phase flow numerical simulation and particle impingement heating prediction in SRM nozzle
Su Penghui, Ai Bangcheng, Pan Honglu
2012, (7): 900-904,909.
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Abstract:
The aluminum oxide particle laden two-phase flow is an important characteristic of the solid rocket motor (SRM) nozzle flow field. Numerical investigations were conducted to understand the two-phase flow field and the surface heat increment caused by particle impingement in SRM nozzle. The Eulerian ...
Application of detached-eddy simulation based on Spalart-Allmaras turbulence model
Chen Jiangtao, Zhang Peihong, Zhou Naichun, Deng Youqi
2012, (7): 905-909.
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Abstract:
The numerical simulation of the high Reynolds number, massively separated flows such as flow over the circular cylinder and supersonic base flow were performed with detached-eddy simulation based on Spalart-Allmaras turbulence model. The inviscid flux was obtained with 2nd order upwind scheme and 2n...
Calculation of steady and unsteady aerodynamic characteristics for ballonets
Song Shuheng, Chen Dehua, Liu Xiaobo
2012, (7): 910-914.
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Abstract:
For ballonets with various shapes at 0~20 km, the incompressible Navier-Stokes(N-S) equations were solved by artificial compressibility approach, and steady and unsteady flow fields around ballonets at five different altitudes were numerically simulated. The ballonet aerodynamic force and the comple...
New method to evaluate crew workload and application
Wang Lijing, Xiang Wei, He Xueli, Li Runshan
2012, (7): 915-919,940.
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Abstract:
Crew workload assessment is an important index of airworthiness certification.Wokload assessment is required by both CFR-25.1523 of federal aviation administration(FAA) airworthiness certification and CCAR-25.1523 of Chinese airworthiness certification. The basic frame of evaluation index system was...
Compressive behaviour of composite cylindrical shell with open hole
Yan Chongnian, Fan Zhou, Cheng Xiaoquan, Li Zhengneng
2012, (7): 920-924.
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Abstract:
The compressive behavior of one-third composite cylindrical shell with opening reinforcement was studied under a compress load. The reinforced specimen was tested and failed in buckling at 65.922 kN near the open hole. A finite element model was established in ABAQUS to investigate the buckling beha...
Aerodynamics of hovering true hoverflies
Mou Xiaolei, Sun Mao
2012, (7): 925-930.
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Abstract:

The aerodynamic force production of true hoverfly which can hover with an inclined stroke plane (body being approximately horizontal) was investigated, using the method of numerically solving the Navier-Stokes equation. The power requirement was computed using the aerodynamic moment and the inertia ...
Progressive damage analysis method and experimental investigation of composite end frame structure
Yang Lei, Yan Ying, Yan Wei, Wang Lipeng
2012, (7): 931-935.
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Aiming at the upper and lower end frames of the grid stiffened composite cylinder, the tensile tests of three kinds of end frame segment models with different sizes and stacking sequence were conducted. Thus the damage forms and ultimate load of the end frames were gained. The progressive damage ana...
Numerical simulation of shear band in amorphous alloy with initially random material imperfections
Yi Min, Shen Zhigang, Guo Yaofeng
2012, (7): 936-940.
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Based on the free volume theory, a constitutive model of amorphous alloy with free volume as an internal variable was developed to be implemented in the finite element simulation by ABAQUS UMAT subroutine. The initial free volume was taken as the variable of material imperfections. And the initial r...
Simulation of ice effects on aircraft controllability
Xu Zhongda, Su Yuan, Cao Yihua
2012, (7): 941-946.
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The aircraft icing parameter was used to describe the ice effects on the aircraft. A nonlinear six degree-of-freedom computational flight dynamics model was built. The aircraft icing parameter was taken into the flight dynamics model to build up a time-varying simulation model. On this basis, two au...
Hygrothermal properties simulation and damage analysis of T300/QY8911 undirectional laminates
Qi Zhongxin, Yan Ying, Liu Yujia, He Mingze
2012, (7): 947-952.
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Flexural properties of T300/QY8911 undirectional laminates were tested under different hygrothermal conditions. Finite element models of composite undirectional laminates under hygrothermal conditions were built. The flexural properties of T300/QY8911 undirectional laminates tested in experimentatio...
Alternating lower-upper splitting iterative method and its application in CFD
Xiang Qian, Wu Songping, Xu Yue
2012, (7): 953-956.
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Small time step is used to ensure convergence in the time-dependent method in computational fluid dynamics(CFD). An improved iteration method termed as the alternating lower-upper splitting (ALUS) iterative method was proposed to address the problem, in which the coefficient matrix was split into a ...
Study and verification on similarity theory for propellers of stratospheric airships
Liu Peiqing, Ma Lichuan, Duan Zhongzhe, Ma Rong
2012, (7): 957-961.
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According to similarity theory of propellers, equal Reynolds number and equal advanced ratio similarity was selected as a group of similarity criterion combination. The effect of different density on the propeller similarity criterion was investigated by using numerical simulation. The chosen simila...
Variable-fidelity optimization applied to wing-body configuration
Zhou Ting, Wu Zongcheng, Chen Zemin, Zhu Ziqiang
2012, (7): 962-965.
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Based on the trust region method, a variable-fidelity optimization method is developed to effectively manage and utilize low-fidelity models and high-fidelity models. The low-fidelity model was employed to build an approximation model in optimization process, while the high-fidelity model was used t...
Derivative artificial compression method of conservation laws
Dong Haitao, Liu Fujun, Han Chong
2012, (7): 966-970.
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Applying high resolution difference schemes on the derivative equations of conservation laws could overcome the shortcoming of accuracy decay at extreme points that has plagued almost all high resolution schemes. Similar to Harten-s artificial compression method, the new method is called derivative ...
Coaxial helicopter model identification based on differential evolution algorithm and accuracy analysis
Liu Peng, Meng Zhijun, Wu Zhe
2012, (7): 971-975.
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The coaxial helicopter exists intense aerodynamic interaction between the upper and lower rotor, and it is difficult to establish the accurate dynamic model for flight control systems using the theory analysis and wind tunnel experiment. Frequency sweep flight experiment data was used to extract the...
Boundary element solution method of free vibration of Timoshenko beam
Jin Jing, Xing Yufeng
2012, (7): 976-980.
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The fundamental solution for free vibration of Timoshenko beam was derived using the Fourier transform. Weighted residual method was adapted to deduce the boundary integral formulation from the control differential equations, from which and using boundary conditions one could find the frequency equa...
Analysis of gravity-assist mechanism based on three-dimension elliptic restricted three-body model
Jia Jianhua, Wang Qi
2012, (7): 981-986.
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A three-dimension elliptic restricted three-body model for the gravity-assist technology in interplanetary exploration was developed based on the planar elliptic restricted three-body model by introducing two extra parameters. By using integrated backward and integrated forward method, the energies ...

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