A hybrid isothermal model for the homogeneous-heterogeneous reactions in ferrohydrodynamic boundary layer ?ow is established. The characteristics of Newtonian heating and magnetic dipole in a ferro?uid due to a stretc...A hybrid isothermal model for the homogeneous-heterogeneous reactions in ferrohydrodynamic boundary layer ?ow is established. The characteristics of Newtonian heating and magnetic dipole in a ferro?uid due to a stretchable surface is analyzed for three chemical species. It is presumed that the isothermal cubic autocatalator kinetic gives the homogeneous reaction and the ?rst order kinetics gives the heterogeneous(surface) reaction. The analysis is carried out for equal diffusion coe?cients of all autocatalyst and reactions. Heat ?ux is examined by incorporating Fourier's law of heat conduction. Characteristics of materialized parameters on the magneto-thermomechanical coupling in the ?ow of a chemically reactive species are investigated. Further, the heat transfer rate and friction drag are depicted for the ferrohydrodynamic chemically reactive species. It is evident that the Schmidt number has increasing behavior on the rate of heat transfer in the boundary layer. Comparison with available results for speci?c cases is found an excellent agreement.展开更多
The dynamic response of offshore platforms is more serious in hostile sea environment than in shallow sea. In this paper, a hybrid solution combined with analytical and numerical method is proposed to compute the stoc...The dynamic response of offshore platforms is more serious in hostile sea environment than in shallow sea. In this paper, a hybrid solution combined with analytical and numerical method is proposed to compute the stochastic response of fixed offshore platforms to random waves, considering wave-structure interaction and non-linear drag force. The simulation program includes two steps: the first step is the eigenanalysis aspects associated the structure and the second step is response estimation based on spectral equations. The eigenanalysis could be done through conventional finite element method conveniently and its natural frequency and mode shapes obtained. In the second part of the process, the solution of the offshore structural response is obtained by iteration of a series of coupled spectral equations. Considering the third-order term in the drag force, the evaluation of the three-fold convolution should be demanded for nonlinear stochastic response analysis. To demonstrate this method, a numerical analysis is carried out for both linear and non-linear platform motions. The final response spectra have the typical two peaks in agreement with reality, indicating that the hybrid method is effective and can be applied to offshore engineering.展开更多
为了探究跨声速飞行工况下混合并联涡轮基组合循环(Turbo based combine cycle,TBCC)动力的冲压流道在冷通气状态下的流动及阻力特性,构建了一个巡航马赫数为4.0、基于混合并联TBCC动力的高马赫数飞机模型,通过三维定常数值模拟方法研...为了探究跨声速飞行工况下混合并联涡轮基组合循环(Turbo based combine cycle,TBCC)动力的冲压流道在冷通气状态下的流动及阻力特性,构建了一个巡航马赫数为4.0、基于混合并联TBCC动力的高马赫数飞机模型,通过三维定常数值模拟方法研究了其在Ma_(∞)=0.7~1.6,H_(∞)=11 km飞行环境下飞机-发动机内/外流动及其耦合特征。计算结果表明:跨声速状态下,冲压进气道入口处气流增压后的静压达到了自由来流滞止压力的85%~90%,气流接近于滞止状态,说明组合进气道存在强烈的节流效应,且冲压通道的喉道是组合进气道节流效应的主要贡献者;冲压发动机尾喷管的排气流动同时受到飞机绕流及涡轮通道排气系统等多方面的干扰,且涡轮通道排气射流对冲压发动机尾喷管气流本身就存在膨胀压缩及排气引射等多种干扰机制。阻力分析表明,压差阻力系数高出内表面摩擦阻力系数2个数量级,是跨声速状态下冲压流道阻力的主要来源;亚声速状态下,进气道阻力占比达到了60%~80%,是冲压流道的主要阻力部件,而Ma_(∞)>1.0超声速状态下,进气道阻力占比随飞行马赫数的增大而逐步减小,尾喷管的阻力则快速增长,阻力贡献逐渐向尾喷管转移,两者趋于接近。展开更多
基金the Higher Education Commission(HEC)under Grant No.6170/Fedral/NRPU/R&D/HEC/2016
文摘A hybrid isothermal model for the homogeneous-heterogeneous reactions in ferrohydrodynamic boundary layer ?ow is established. The characteristics of Newtonian heating and magnetic dipole in a ferro?uid due to a stretchable surface is analyzed for three chemical species. It is presumed that the isothermal cubic autocatalator kinetic gives the homogeneous reaction and the ?rst order kinetics gives the heterogeneous(surface) reaction. The analysis is carried out for equal diffusion coe?cients of all autocatalyst and reactions. Heat ?ux is examined by incorporating Fourier's law of heat conduction. Characteristics of materialized parameters on the magneto-thermomechanical coupling in the ?ow of a chemically reactive species are investigated. Further, the heat transfer rate and friction drag are depicted for the ferrohydrodynamic chemically reactive species. It is evident that the Schmidt number has increasing behavior on the rate of heat transfer in the boundary layer. Comparison with available results for speci?c cases is found an excellent agreement.
基金National Natural Science Foundation of China(Grant No.59895410,59779002)
文摘The dynamic response of offshore platforms is more serious in hostile sea environment than in shallow sea. In this paper, a hybrid solution combined with analytical and numerical method is proposed to compute the stochastic response of fixed offshore platforms to random waves, considering wave-structure interaction and non-linear drag force. The simulation program includes two steps: the first step is the eigenanalysis aspects associated the structure and the second step is response estimation based on spectral equations. The eigenanalysis could be done through conventional finite element method conveniently and its natural frequency and mode shapes obtained. In the second part of the process, the solution of the offshore structural response is obtained by iteration of a series of coupled spectral equations. Considering the third-order term in the drag force, the evaluation of the three-fold convolution should be demanded for nonlinear stochastic response analysis. To demonstrate this method, a numerical analysis is carried out for both linear and non-linear platform motions. The final response spectra have the typical two peaks in agreement with reality, indicating that the hybrid method is effective and can be applied to offshore engineering.
文摘为了探究跨声速飞行工况下混合并联涡轮基组合循环(Turbo based combine cycle,TBCC)动力的冲压流道在冷通气状态下的流动及阻力特性,构建了一个巡航马赫数为4.0、基于混合并联TBCC动力的高马赫数飞机模型,通过三维定常数值模拟方法研究了其在Ma_(∞)=0.7~1.6,H_(∞)=11 km飞行环境下飞机-发动机内/外流动及其耦合特征。计算结果表明:跨声速状态下,冲压进气道入口处气流增压后的静压达到了自由来流滞止压力的85%~90%,气流接近于滞止状态,说明组合进气道存在强烈的节流效应,且冲压通道的喉道是组合进气道节流效应的主要贡献者;冲压发动机尾喷管的排气流动同时受到飞机绕流及涡轮通道排气系统等多方面的干扰,且涡轮通道排气射流对冲压发动机尾喷管气流本身就存在膨胀压缩及排气引射等多种干扰机制。阻力分析表明,压差阻力系数高出内表面摩擦阻力系数2个数量级,是跨声速状态下冲压流道阻力的主要来源;亚声速状态下,进气道阻力占比达到了60%~80%,是冲压流道的主要阻力部件,而Ma_(∞)>1.0超声速状态下,进气道阻力占比随飞行马赫数的增大而逐步减小,尾喷管的阻力则快速增长,阻力贡献逐渐向尾喷管转移,两者趋于接近。
