Effects of wall temperature on boundary layer stability over a blunt cone at Mach 7.99

Effects of wall temperature on stabilities of hypersonic boundary layer over a 7-degree half-cone-angle blunt cone are studied by using both direct numerical simulation (DNS) and linear stability theory (LST) analysis. Four isothermal wall cases with Tw/T0= 0.5, 0.7, 0.8 and 0.9, as well as an adiabatic wall case are considered. Results of both DNS and LST indicate that wall temperature has significant effects on the growth of disturbance waves. Cooling the surface accelerates unstable Mack II mode waves and decelerates the first mode (Tollmien–Schlichting mode) waves. LST results show that growth rate of the most unstable Mack II mode waves for the cases of cold wall Tw/T0=0.5 and 0.7 are about 45% and 25% larger than that for the adiabatic wall, respectively. Numerical results show that surface cooling modifies the profiles of rdut/dyn and temperature in the boundary layers, and thus changes the stability haracteristic of the boundary layers, and then effects on the growth of unstable waves. The results of DNS indicate that the disturbances with the frequency range from about 119.4 to 179.1 kHz, including the most unstable Mack modes, produce strong mode competition in the downstream region from about 11 to 100 nose radii. And adiabatic wall enhances the amplitudes of disturbance according to the results of DNS, although the LST indicates that the growth rate of the disturbance of cold wall is larger. That because the growth of the disturbance does not only depend on the development of the second unstable mode

Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack

The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [Li et al., AIAA J. 46, 2899(2008)], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 0° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves VLFWs� are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough.The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [ Li et al., AIAA J. 46, 2899 (2008) ], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 20° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves (VLFWs) are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough

非线性优化的保单调差分格式

采用保单调思想，结合非线性优化，构造了六阶精度的保单调差分格式(OMP6). 格式构造过程中采用非线性Forier 分析对格式的色散及耗散误差进行了优化。通过Shu-Osher,双Mach 反射以及RT不稳定性等算例对该格式进行了验证。算例表明，与常用的WENO 等格式相比，该格式(OMP6)具有格式简洁、计算量小、分辨率高等优点

中国新一轮企业所得税改革:一个公司治理的视角

税制总是随着所处的政治、经济、文化、技术环境的变化而不断优化和调整。2003年10月,中国启动了新一轮税制改革。本文在对税收与公司治理结构相关研究进行综述的基础上,从改善中国公司治理结构的视角,指出中国新一轮企业所得税改革需要关注的几个问题。湖北省科技厅引导项目(项目批准号:2006AA412C05

A New High Order Accurate Shock Capture Method with Wave Booster

A new kind of shock capturing method is developed. Before applying the high order accurate traditional scheme which is called as base scheme in this paper the fluid parameters are preconditioned in order to control the group velocity. The newly constructed scheme is high order accurate, simple, has high resolution of the shock, and less computer time consumed

优化的保单调差分格式及激波/湍流边界层干扰的直接数值模拟

基于色散及耗散的非线性优化及保单调技术,构造了6阶精度的优化保单调差分格式(OMP6)。通过Shu-Osher,双Mach反射,R-T不稳定问题对格式进行了测试。算例表明,与目前常用的7阶WENO格式相比,OMP6在激波及小尺度波分辨率上具有一定优势,且计算效率有了明显提高,是进行可压缩复杂流动高分辨率数值模拟的良好候选方法。运用该方法,进行了激波-湍流边界层干扰的直

超声速压缩拐角激波/边界层干扰动力学模态分解

压缩拐角激波与边界层干扰问题广泛存在于高速飞行器的外部和内部流动中,其非定常复杂流场结构对飞行器气动性能影响显著。动力学模态分析将有助于进一步加深理解激波与边界层干扰流场不同特征频率对应的流动结构及动力学特性,为揭示其复杂流动机理提供参考。本文采用动态模态分解（DMD）方法对来流马赫数为2.9、24°压缩拐角内激波与超声速边界层干扰下的非定常流动进行了模态分析。评估了稀疏改进动态模态分解方法在压缩拐角流动中的适用性,研究了湍流干扰和转捩干扰下典型特征频率对应的动力学模态空间结构差异及其原因,分析了转捩边界层展向非均匀性对低频/高频模态动力学机制的影响规律。研究发现,湍流干扰与转捩干扰下拐角干扰区内均存在两类截然不同的动力学模态：低频模态和高频模态。低频模态结构集中在分离激波及分离泡剪切层的根部,表征为分离泡的大尺度膨胀和收缩运动;高频模态空间分布则以平均声速线附近正负交替结构为主,对应为边界层内不稳定波沿剪切层往下游的传播。转捩边界层的展向结构对低频模态运动特性影响明显,而对高频模态的影响则相对较小

分辨率优化的混合WENO格式

为提高有限差分格式的分辨率,利用傅里叶分析对WENO格式进行色散及耗散优化,并给出优化的线性权重.用优化后的WENO格式与保单调格式（MP）进行加权混合,得到新的加权混合WENO格式（H-WENO）.通过一维激波管问题、Shu-Osher问题及二维双Mach反射问题及R-T不稳定性问题对格式进行数值测试.结果显示,新格式具有强健的激波捕捉能力和对小尺度波结构的高分辨率,与原WENO格式相比改进明显

压缩拐角激波与旁路转捩边界层干扰数值研究

为了研究激波与旁路转捩边界层的干扰机理,采用直接数值模拟(DNS)方法对来流马赫数Ma∞=2.9,24°压缩拐角内激波与转捩边界层的相互作用进行了系统的研究。考察了旁路转捩干扰下压缩拐角内分离区形态和激波波系结构的典型特征。比较了转捩干扰与湍流干扰流动结构的差异,并分析了造成差异的原因。研究了拐角内转捩边界层的演化特性,探讨了转捩干扰下脉动峰值压力和峰值摩阻的分布规律及形成机制。研究结果表明:相较于湍流干扰,两侧发卡涡串的展向挤压使得分离区起始点以V字型分布,且分离激波沿展向以破碎状态为主,激波脚呈现多层结构;拐角内的干扰作用急剧加速了边界层的转捩过程;转捩干扰下的拐角内峰值脉动压力以单峰结构出现在分离区的下游,同时干扰区内的强湍动能和高雷诺剪切应力使得其局部峰值摩阻系数要高于湍流干扰

Dynamic optimization methodology based on subgrid-scale dissipation for large eddy simulation

A dynamic procedure based on subgrid-scale dissipation is proposed for large eddy simulation of turbulent flows. In the new method, the model coefficients are determined by minimizing the square error of the resolved dissipation rate based on the Germano identity. A dynamic two-term mixed model is tested and evaluated both a priori and a posteriori in simulations of homogeneous and isotropic turbulence. The new dynamic procedure proves to be more effective to optimize the model coefficients as compared with traditional method. The corresponding dynamic mixed model can predict the physical quantities more accurately than traditional dynamic mixed model. (C) 2016 AIP Publishing LLC