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| 1 | A Numerical Research on a Compressibility-correlated Langtry's Transition Model for Double Wedge Boundary Layer Flows显示文摘新压缩的可能性关联在 Langtry 的本地基于变量的转变模型被介绍在两倍楔吃惊 / 边界层相互作用上调查现象。计算分析与试验性的数据相比被做了在极超音速的双楔边界层上估计墙温度和前缘鼻子半径的影响。laminar 边界层分离发生在第一个斜面上,这被发现了。而且,墙温度和前缘鼻子半径在纽结在分离特征上有显著影响。当使用修改转变模型时,有试验性的数据的计算压力系数分发和边界层侧面的比较证明更好的结果能被完成。 | ZHANG Xiaodong GAO Zhenghong | 2011 | Chinese Journal of Aeronautics2011，24，3： | 16 |
| 2 | Aerodynamic multi-objective integrated optimization based on principal component analysis显示文摘Based on improved multi-objective particle swarm optimization(MOPSO) algorithm with principal component analysis(PCA) methodology, an efficient high-dimension multiobjective optimization method is proposed, which, as the purpose of this paper, aims to improve the convergence of Pareto front in multi-objective optimization design. The mathematical efficiency,the physical reasonableness and the reliability in dealing with redundant objectives of PCA are verified by typical DTLZ5 test function and multi-objective correlation analysis of supercritical airfoil,and the proposed method is integrated into aircraft multi-disciplinary design(AMDEsign) platform, which contains aerodynamics, stealth and structure weight analysis and optimization module.Then the proposed method is used for the multi-point integrated aerodynamic optimization of a wide-body passenger aircraft, in which the redundant objectives identified by PCA are transformed to optimization constraints, and several design methods are compared. The design results illustrate that the strategy used in this paper is sufficient and multi-point design requirements of the passenger aircraft are reached. The visualization level of non-dominant Pareto set is improved by effectively reducing the dimension without losing the primary feature of the problem. | Jiangtao HUANG Zhu ZHOU Zhenghong GAO Miao ZHANG Lei YU | 2017 | Chinese Journal of Aeronautics2017，30，4： | 10 |
| 3 | Aerodynamic design optimization of nacelle/pylon position on an aircraft显示文摘The arbitrary space-shape free form deformation (FFD) method developed in this paper is based on non-uniform rational B-splines (NURBS) basis function and used for the integral parameterization of nacelle-pylon geometry. The multi-block structured grid deformation technique is established by Delaunay graph mapping method. The optimization objects of aerodynamic characteristics are evaluated by solving NavierStokes equations on the basis of multi-block structured grid. The advanced particle swarm optimization (PSO) is utilized as search algorithm, which com-bines the Kriging model as surrogate model during optimization. The optimization system is used for optimizing the nacelle location of DLR-F6 wing-body-pylon-nacelle. The results indicate that the aerodynamic interference between the parts is significantly reduced. The optimization design system established in this paper has extensive applications and engineering value. | Li Jing Gao Zhenghong Huang Jiangtao Zhao Ke | 2013 | Chinese Journal of Aeronautics2013，26，4： | 10 |
| 4 | Research on multi-fidelity aerodynamic optimization methods显示文摘Constructing high approximation accuracy surrogate model with lower computational cost has great engineering significance. In this paper, using co-Kriging method, an efficient multi-fidelity surrogate model is constructed based on two independent high and low fidelity samples. Co-Kriging method can use a greater quantity of low-fidelity information to enhance the accuracy of a surrogate of the high-fidelity model by modeling the correlation between high and low fidelity model, thus computational cost of building surrogate model can be greatly reduced. A wing-body problem is taken as an example to compare characteristics of co-Kriging multi-fidelity (CKMF) model with traditional Kriging based multi-fidelity (KMF) model. A sampling convergence of the CKMF model and the KMF model is conducted, and an appropriate sampling design is selected through the sampling convergence analysis. The results indicate that CKMF model has higher approximation accuracy with the same high-fidelity samples, and converges at less high-fidelity samples. A wing-body drag reduction optimization design using genetic algorithm is implemented. Satisfying design results are obtained, which validate the feasibility of CKMF model in engineering design. | Huang Likeng Gao Zhenghong Zhang Dehu | 2013 | Chinese Journal of Aeronautics2013，26，2： | 9 |
| 5 | Robust design of NLF airfoils显示文摘A robust optimization design approach of natural laminar airfoils is developed in this paper. First, the non-uniform rational B-splines (NURBS) free form deformation method based on NURBS basis function is introduced to the airfoil parameterization. Second, aerodynamic characteristics are evaluated by solving Navier-Stokes equations, and theγ-Reθt transition model coupling with shear-stress transport (SST) turbulent model is introduced to simulate boundary layer transition. A numerical simulation of transition flow around NLF0416 airfoil is conducted to test the code. The comparison between numerical simulation results and wind tunnel test data approves the validity and applicability of the present transition model. Third, the optimization system is set up, which uses the separated particle swarm optimization (SPSO) as search algorithm and combines the Kriging models as surrogate model during optimization. The system is applied to carry out robust design about the uncertainty of lift coefficient and Mach number for NASA NLF-0115 airfoil. The data of optimized airfoil aerodynamic characteristics indicates that the optimized airfoil can maintain laminar flow stably in an uncertain range and has a wider range of low drag. | Li Jing Gao Zhenghong Huang Jiangtao Zhao Ke | 2013 | Chinese Journal of Aeronautics2013，26，2： | 9 |
| 6 | Double-stage Metamodel and Its Application in Aerodynamic Design Optimization显示文摘Constructing metamodel with global high-fidelity in design space is significant in engineering design. In this paper, a double-stage metamodel (DSM) which integrates advantages of both interpolation metamodel and regression metamodel is constructed. It takes regression model as the first stage to fit overall distribution of the original model, and then interpolation model of regression model approximation error is used as the second stage to improve accuracy. Under the same conditions and with the same samples, DSM expresses higher fidelity and represents physical characteristics of original model better. Besides, in order to validate DSM characteristics, three examples including Ackley function, airfoil aerodynamic analysis and wing aerody-namic analysis are investigated. In the end, airfoil and wing aerodynamic design optimizations using genetic algorithm are presented to verify the engineering applicability of DSM. | ZHANG Dehu GAO Zhenghong HUANG Likeng WANG Mingliang | 2011 | Chinese Journal of Aeronautics2011，24，5： | 8 |
| 7 | Inverse design of low boom configurations using proper orthogonal decomposition and augmented Burgers equation显示文摘Mitigation of sonic boom to an acceptable stage is a key point for the next generation of supersonic transports. Meanwhile, designing a supersonic aircraft with an ideal ground signature is always the focus of research on sonic boom reduction. This paper presents an inverse design approach to optimize the near-field signature of an aircraft, making it close to the shaped ideal ground signature after the propagation in the atmosphere. Using the Proper Orthogonal Decomposition(POD) method, a guessed input of augmented Burgers equation is inversely achieved. By multiple POD iterations, the guessed ground signatures successively approach the target ground signature until the convergence criteria is reached. Finally, the corresponding equivalent area distribution is calculated from the optimal near-field signature through the classical Whitham F-function theory. To validate this method, an optimization example of Lockheed Martin 1021 is demonstrated. The modified configuration has a fully shaped ground signature and achieves a drop of perceived loudness by 7.94 PLdB. This improvement is achieved via shaping the original near-field signature into wiggles and damping it by atmospheric attenuation. At last, a nonphysical ground signature is set as the target to test the robustness of this inverse design method and shows that this method is robust enough for various inputs. | Yidian ZHANG Jiangtao HUANG Zhenghong GAO Chao WANG Bowen SHU | 2019 | Chinese Journal of Aeronautics2019，32，6： | 7 |
| 8 | Aerodynamic optimization of rotor airfoil based on multi-layer hierarchical constraint method显示文摘Rotor airfoil design is investigated in this paper. There are many difficulties for this highdimensional multi-objective problem when traditional multi-objective optimization methods are used. Therefore, a multi-layer hierarchical constraint method is proposed by coupling principal component analysis(PCA) dimensionality reduction and e-constraint method to translate the original high-dimensional problem into a bi-objective problem. This paper selects the main design objectives by conducting PCA to the preliminary solution of original problem with consideration of the priority of design objectives. According to the e-constraint method, the design model is established by treating the two top-ranking design goals as objective and others as variable constraints. A series of bi-objective Pareto curves will be obtained by changing the variable constraints, and the favorable solution can be obtained by analyzing Pareto curve spectrum. This method is applied to the rotor airfoil design and makes great improvement in aerodynamic performance. It is shown that the method is convenient and efficient, beyond which, it facilitates decision-making of the highdimensional multi-objective engineering problem. | Zhao Ke Gao Zhenghong Huang Jiangtao Li Quan | 2016 | Chinese Journal of Aeronautics2016，29，6： | 7 |
| 9 | Mechanism of unconventional aerodynamic characteristics of an elliptic airfoil显示文摘Abstract The aerodynamic characteristics of elliptic airfoil are quite different from the case of conventional airfoil for Reynolds number varying from about 10~4to 10~6.In order to reveal the fundamental mechanism,the unsteady flow around a stationary two-dimensional elliptic airfoil with 16%relative thickness has been simulated using unsteady Reynolds-averaged Navier–Stokes equations and the γ-Reθt transition turbulence model at different angles of attack for flow Reynolds number of 5×10~5.The aerodynamic coefficients and the pressure distribution obtained by computation are in good agreement with experimental data,which indicates that the numerical method works well.Through this study,the mechanism of the unconventional aerodynamic characteristics of airfoil is analyzed and discussed based on the computational predictions coupled with the wind tunnel results.It is considered that the boundary layer transition at the leading edge and the unsteady flow separation vortices at the trailing edge are the causes of the case.Furthermore,a valuable insight into the physics of how the flow behavior affects the elliptic airfoil’s aerodynamics is provided. | Sun Wei Gao Zhenghong Du Yiming Xu Fang | 2015 | Chinese Journal of Aeronautics2015，28，3： | 6 |
| 10 | Boundary-layer transition of advanced fighter wings at high-speed cruise conditions显示文摘The achievement of laminar flow in the boundary layer at high-speed cruise conditions may further, in addition to shock-wave control, reduce the drag and extend the range of military fighter aircraft. To this end, a further investigation on transitional boundary-layer flow of fighter wings is needed due to different configurations from the wings used on conventional transport aircraft. In this paper, wind tunnel experiments and numerical simulations were conducted on three-dimensional transition of thin diamond-shaped wings used on advanced fighter aircraft at tran/supersonic design points. A newly proposed correlation of crossflow transition which includes the effect of surface roughness was introduced into the c-Rehttransition model. Predicted results were in good agreement with flow visualizations. Results showed that the strength of the crossflow component grew rapidly around the leading edge because of the severe flow acceleration, just as the same as wings with a large aspect ratio. However, there seemed no regular pattern of instabilitydominance variation in span-wise for a diamond configuration. The dominance of different instability mechanisms strongly depended on the local pressure distribution. Hereby, the research recommended a ‘‘roof-like' shape of pressure distribution to suppress both crossflow and Tollmien-Schlichting(T-S) instabilities. Besides, a sharp suction peak with a serious pressure rise should be cut off to avoid stronger instabilities. Further discussions also revealed an independence of the unit Reynolds number when transition was triggered by T-S instabilities. Aerodynamic force comparisons indicated that further benefit on drag reduction could be expected by including the three-dimensional transition effect into a wing design process. | Yiming DU Zhenghong GAO Chao WANG Qianhuan HUANG | 2019 | Chinese Journal of Aeronautics2019，32，4： | 5 |
| 11 | A low-diffusion robust flux splitting scheme towards wide-ranging Mach number flows显示文摘This paper develops a low-diffusion robust flux splitting scheme termed TVAP to achieve the simulation of wide-ranging Mach number flows.Based on Toro-Vazquez splitting approach,the new scheme splits inviscid flux into convective system and pressure system.This method introduces Mach number splitting function and numerical sound speed to evaluate advection system.Meanwhile,pressure diffusion term,pressure momentum flux,interface pressure and interface velocity are constructed to measure pressure system.Then,typical test problems are utilized to systematically assess the robustness and accuracy of the resulting scheme.Matrix stability analysis and a series of numerical cases,such as double shear-layer problem and hypersonic viscous flow over blunt cone,demonstrate that TVAP scheme achieves excellent low diffusion,shock stability,contact discontinuity and low-speed resolution,and is potentially a good candidate for wide-ranging Mach number flows. | Shusheng CHEN Fangjie CAI Xinghao XIANG Zhenghong GAO Chao YAN | 2021 | Chinese Journal of Aeronautics2021，34，5： | 4 |
| 12 | Serum levels of suppressor of cytokine signaling 3 and signal transducer and activator of transcription 3 in childhood atopic dermatitis显示文摘Suppressor of cytokine signaling 3 (SOCS3) proteins,a member of SOCS family,are predominantly expressed in Th2 cells,and it has an important role in regulating the onset and maintenance of Th2-mediated allergic immune disease.1 SOCS can translocate from cytoplasm to nucleus when the level in cytoplasm increases,and localize to cell membrane where it binds to receptors.However,to our knowledge,there has been no documentation whether SOCS can transport to the intercellular space or circulating body fluids,let alone the subsequent biological significance.Signal transducer and activator of transcription (STAT) proteins,a group of transcription factor,are critical for mediating signals during Th1,Th2,Treg,and Th17 differentiation.Recent study demonstrated that STAT3 is not only required for the differentiation of Th17,IL-6-activated STAT3 promotes Maf expression,a factor required for Th2 differentiation and production of IL-4.Furthermore,STAT3 was activated throughout Th2 cell differentiation and was indispensable for Th2 cytokine production and transcription factor expression.2 SOCS proteins were recognized to negatively regulate the JAK/STAT signaling pathway through the common SH2 domain.Since binding of the SH2 domain of SOCS3 is relatively specific to receptors for STAT3-activating cytokines,such as IL-6,granulocyte-colony stimulating factor,leptin,and leukemia inhibitory factor,the suppressive effect of SOCS3 has been shown to be relatively restricted to STAT3.3 In this report we demonstrate that the serum levels of SOCS3 and STAT3 were increased in childhood atopic dermatitis (AD) compared with controls.Furthermore,STAT3 is significantly positively correlated with Scoring Atopic Dermatitis (SCORAD) index. | Lyu Yani Zhu Lili Qi Ruiqun Xu Jing Di Zhenghong Chen Hongduo Gao Xinghua | 2014 | Chinese Medical Journal2014，，12： | 4 |
| 13 | Unstable unsteady aerodynamic modeling based on least squares support vector machines with general excitation显示文摘Common,unsteady aerodynamic modeling methods usually use wind tunnel test data from forced vibration tests to predict stable hysteresis loop.However,these methods ignore the initial unstable process of entering the hysteresis loop that exists in the actual maneuvering process of the aircraft.Here,an excitation input suitable for nonlinear system identification is introduced to model unsteady aerodynamic forces with any motion in the amplitude and frequency ranges based on the Least Squares Support Vector Machines(LS-SVMs).In the selection of the input form,avoiding the use of reduced frequency as a parameter makes the model more universal.After model training is completed,the method is applied to predict the lift coefficient,drag coefficient and pitching moment coefficient of the RAE2822 airfoil,in sine and sweep motions under the conditions of plunging and pitching at Mach number 0.8.The predicted results of the initial unstable process and the final stable process are in close agreement with the Computational Fluid Dynamics(CFD)data,demonstrating the feasibility of the model for nonlinear unsteady aerodynamics modeling and the effectiveness of the input design approach. | Senlin CHEN Zhenghong GAO Xinqi ZHU Yiming DU Chao PANG | 2020 | Chinese Journal of Aeronautics2020，33，10： | 4 |
| 14 | Flight dynamics characteristics of canard rotor/wing aircraft in helicopter flight mode显示文摘The aerodynamic layout of the Canard Rotor/Wing(CRW) aircraft in helicopter flight mode differs significantly from that of conventional helicopters. In order to study the flight dynamics characteristics of CRW aircraft in helicopter mode, first, the aerodynamic model of the main rotor system is established based on the blade element theory and wind tunnel test results. The aerodynamic forces and moments of the canard wing, horizontal tail, vertical tail and fuselage are obtained via theoretical analysis and empirical formula. The flight dynamics model of the CRW aircraft in helicopter mode is developed and validated by flight test data. Next, a method of model trimming using an optimization algorithm is proposed. The flight dynamics characteristics of the CRW are investigated by the method of linearized small perturbations via Simulink. The trim results are consistent with the conventional helicopter characteristics, and the results show that with increasing forward flight speed, the canard wing and horizontal tail can provide considerable lift,which reflects the unique characteristics of the CRW aircraft. Finally, mode analysis is implemented for the linearized CRW in helicopter mode. The results demonstrate that the stability of majority modes increases with increasing flight speed. However, one mode that diverges monotonously,and the reason is that the CRW helicopter mode has a large vertical tail compared to the conventional helicopter. The results of the dynamic analysis provide optimization guidance and reference for the overall design of the CRW aircraft in helicopter mode, and the model developed can be used for control system design. | Honggang GAO Ao HE Zhenghong GAO Yang NA Yangping DENG | 2019 | Chinese Journal of Aeronautics2019，32，7： | 3 |
| 15 | Buffeting numerical simulation coupled with aerodynamics and structure based on MDDES显示文摘Unsteady effect of seriously separated flow is the main factor of modern aircraft buffeting. So accurate simulation of this complex flow becomes the basis associated with the research of aircraft buffeting. This paper constructs an unsteady numerical simulation method for separation flow based on modified delayed detached eddy simulation (MDDES) method by considering both modern computer resources and the credibility of simulating separation flow. The proposed method is also verified through the simulation of the separated flow by a typical fighter at high angle of attack. And then a robust and efficient technology for deforming mesh is established using radial basis function (RBF) and infinite interpolation method. Moreover, the platform for numerical simulation of buffeting is set up in combination with the structural dynamics equations in the modal space, by which the research of vertical tail buffeting caused by edge vortex is carried out on a fighter at large angle of attack. Through spectrum analysis of time-domain response of pressure pulsation on the location of vortex rupture, the results show that the pulsation frequency of vortex structure with different scales covers the inherent modal frequency of vertical tail structure. Compared to the Reynolds-averaged Navier-Stokes equations, the MDDES method can distinguish the more detailed and higher frequency small-scale vortex structure. Unlike flutter, displacement acceleration response of each mode in buffeting is dominated by its own mode. There exists strong coupling between the first bending mode and first torsion mode, and it leads to acceleration and large inertia impact of structure, which is the main factor causing structural fatigue. In sum, the obtained results verify the validity of the numerical means and the corresponding methods in the paper. | HUANG JiangTao GAO ZhengHong | 2013 | Science China(Technological Sciences)2013，56，6： | 3 |
| 16 | An improved adaptive sampling and experiment design method for aerodynamic optimization显示文摘Experiment design method is a key to construct a highly reliable surrogate model for numerical optimization in large-scale project. Within the method, the experimental design criterion directly affects the accuracy of the surrogate model and the optimization efficient. According to the shortcomings of the traditional experimental design, an improved adaptive sampling method is proposed in this paper. The surrogate model is firstly constructed by basic sparse samples. Then the supplementary sampling position is detected according to the specified criteria, which introduces the energy function and curvature sampling criteria based on radial basis function(RBF) network.Sampling detection criteria considers both the uniformity of sample distribution and the description of hypersurface curvature so as to significantly improve the prediction accuracy of the surrogate model with much less samples. For the surrogate model constructed with sparse samples, the sample uniformity is an important factor to the interpolation accuracy in the initial stage of adaptive sampling and surrogate model training. Along with the improvement of uniformity, the curvature description of objective function surface gradually becomes more important. In consideration of these issues, crowdness enhance function and root mean square error(RMSE) feedback function are introduced in C criterion expression. Thus, a new sampling method called RMSE and crowdness enhance(RCE) adaptive sampling is established. The validity of RCE adaptive sampling method is studied through typical test function firstly and then the airfoil/wing aerodynamic optimization design problem, which has high-dimensional design space. The results show that RCE adaptive sampling method not only reduces the requirement for the number of samples, but also effectively improves the prediction accuracy of the surrogate model, which has a broad prospects for applications. | Huang Jiangtao Gao Zhenghong Zhou Zhu Zhao Ke | 2015 | Chinese Journal of Aeronautics2015，28，5： | 3 |
| 17 | Variable-fidelity optimization with design space reduction显示文摘Advanced engineering systems, like aircraft, are defined by tens or even hundreds of design variables. Building an accurate surrogate model for use in such high-dimensional optimization problems is a difficult task owing to the curse of dimensionality. This paper presents a new algorithm to reduce the size of a design space to a smaller region of interest allowing a more accurate surrogate model to be generated. The framework requires a set of models of different physical or numerical fidelities. The low-fidelity (LF) model provides physics-based approximation of the high-fidelity (HF) model at a fraction of the computational cost. It is also instrumental in identifying the small region of interest in the design space that encloses the high-fidelity optimum. A surrogate model is then constructed to match the low-fidelity model to the high-fidelity model in the identified region of interest. The optimization process is managed by an update strategy to prevent convergence to false optima. The algorithm is applied on mathematical problems and a two-dimen-sional aerodynamic shape optimization problem in a variable-fidelity context. Results obtained are in excellent agreement with high-fidelity results, even with lower-fidelity flow solvers, while showing up to 39% time savings. | Mohammad Kashif Zahir Gao Zhenghong | 2013 | Chinese Journal of Aeronautics2013，26，4： | 2 |
| 18 | Characteristics of array of distributed synthetic jets and effect on turbulent boundary layer显示文摘An array of distributed round synthetic jets was used to control a fully developed turbulent boundary layer.The study focused on the related skin friction drag reduction and mechanisms involved.The control effects were analyzed by measuring the streamwise velocities using a hot-wire anemometer downstream of the array.A reduction in the skin friction was observed both in the regions downstream of the orifices and in the regions between two adjacent orifices.A statistical analysis with the variable-interval time-averaging(VITA)technique demonstrated a weakened bursting intensity with synthetic jet in the near-wall region.The streamwise vortices were lifted by the upwash effect caused by synthetic jet and induced less low-speed streaks.The control mechanism acted in a way to suppress the dynamic interaction between the streamwise vortices and low-speed streaks and to attenuate the turbulence production in the near-wall region.The forcing frequency was found to be a more relevant parameter when synthetic jet was applied in turbulent boundary layer flow control.A higher forcing frequency induced a higher reduction in the skin friction.The power spectral density and autocorrelation of the fluctuating velocities showed that the synthetic jets gradually decayed in the streamwise direction,having an effect as far as 34.5 times the displacement thickness that was on the trailing edge of the distributed synthetic jets array. | Lianshan Lu Dong Li Zhenghong Gao Zhen Cao Yu Bai Jie Zheng | 2020 | Acta Mechanica Sinica2020，36，6： | 2 |
| 19 | Hybrid photoanode films based on sparse ZnO rod array-TiO_2 nanoparticles in dye-sensitized solar cells显示文摘ZnO-TiO2 hybrid photoanodes were fabricated via the doctor-blade method by integrating vertically-grown sparse ZnO arrays with hydrothermal TiO2 nanoparticles. A special surface-coating technique was developed to deposit a thin TiO2 layer on the surface of ZnO rods. Microstructure, optical and photoelectrochemical performance of the hybrid photoanodes were investigated. The denser ZnO array exhibited bad filling behavior of nanoparticles in the interspace of ZnO rods, strong scattering and low conversion efficiency (0.27%). The sparser array showed a much better integrated microstructure, improved transmittance and high conversion efficiency (2.68%). The surface modification of ZnO rods by the TiO2 thin layer was found useful in improving the interfacial microstructure between the ZnO rod and the TiO2 bulk film, and the total conversion efficiency of 3.01% was achieved, higher than that of the pure TiO2 nanoparticle cell (2.93%). The increased scattering effects on the incident light, the enhanced electron transportation at TiO2/dye/electrolyte interface, and the inhabited recombination were responsible for this improvement. | WANG CaiLu GAO XiangDong LI XiaoMin JIANG ZhengWu YANG ZhengHong GU ZhengYing HE Peng | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，7： | 2 |
| 20 | A new grid deformation technology with high quality and robustness based on quaternion显示文摘Quality and robustness of grid deformation is of the most importance in the field of aircraft design, and grid in high quality is essential for improving the precision of numerical simulation. In order to maintain the orthogonality of deformed grid, the displacement of grid points is divided into rotational and translational parts in this paper, and inverse distance weighted interpolation is used to transfer the changing location from boundary grid to the spatial grid. Moreover, the deformation of rotational part is implemented in combination with the exponential space mapping that improves the certainty and stability of quaternion interpolation. Furthermore, the new grid deformation technique named ‘‘layering blend deformation'' is built based on the basic quaternion technique, which combines the layering arithmetic with transfinite interpolation(TFI) technique. Then the proposed technique is applied in the movement of airfoil, parametric modeling, and the deformation of complex configuration, in which the robustness of grid quality is tested. The results show that the new method has the capacity to deal with the problems with large deformation, and the ‘‘layering blend deformation'' improves the efficiency and quality of the basic quaternion deformation method significantly. | Huang Jiangtao Gao Zhenghong Wang Chao | 2014 | Chinese Journal of Aeronautics2014，27，5： | 2 |
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