高航速流动不分离外形带攻角流动特性分析

边界层发生分离的两个必要条件是流体粘性和正压梯度,设计外形使其表面具有尽量大的负压梯度区域,延缓边界层转捩和流动分离,从而达到减阻目的。本文采用基于细长体理论的流动不分离外形设计方法,设计临界速度为100 m/s的航行体外形,运用数值仿真分析其在不同速度和攻角情况下的流动特性。研究发现,0°攻角下仿真得到的压强分布与理论计算结果一致,摩擦阻力与估算结果一致,证明可以通过外形设计使航行体边界层在高雷诺数条件下保持层流流动不分离状态,以达到大幅减阻的目的;小攻角不会破坏航行体表面流体附着状态,但攻角会使流动出现横向漩涡,边界层发生转捩,使阻力明显增加,但减阻效果仍然存在。

基于负压梯度翼型栅格翼设计与水中数值分析

为改善栅格翼的水动力性能,基于流动不分离理论设计了负压梯度翼型,并将其运用于栅格翼的设计;数值模拟研究了该翼型与NACA0015翼型在一定的空化数和攻角条件下的升阻及压力分布特性;探究了3种叶片间距的负压梯度翼型栅格翼在不同攻角下的升阻、压力及空泡几何形状。结果表明,含攻角时,该翼型对应的临界空化数要比NACA0015的小,但二者升阻系数基本一致;小攻角情况下,栅格翼叶片数量增加时升力会趋于一常值,但阻力会不断增加;大攻角情况下,叶片数量的增加会导致升力和阻力均明显增加。对于同一叶片间距的栅格翼,攻角越大,栅格翼叶片由上至下空泡的长度和厚度减小的速率越大。对于不同叶片间距的栅格翼,叶片数量越大,各个叶片的压力干扰越剧烈,压差阻力越大,导致升阻比降低。同时,剧烈的压力干扰会导致栅格翼的空泡长度增加。因此,在满足水动力特性要求时,基于该文翼型设计负压梯度翼型栅格翼应尽量减少叶片数量。

GPU-based discrete element simulation on flow stability of flat-bottomed hopper

In this study, the flow stability of the flat-bottomed hopper was investigated via GPU-based discrete element method(DEM) simulation. With the material height inside the hopper reducing, the fluctuation of the flow rate indicates an unstable discharge. The flow regions of the unstable discharge were compared with that of the stable discharge, a key transformation zone, where the voidage showed the largest difference between unstable and stable discharge, was revealed. To identify the relevance of the key transformation zone and the hopper flow stability, the voidage variation of the key transformation zone with material height reducing was studied.A sharp increase in the voidage in the key transformation zone was considered to be the standard for judging the unstable hopper flow, and the ‘Top–Bottom effect' of the hopper was defined, which indicated the hopper flow was unstable when the hopper only had the top area and the bottom area, because the voidage of particles in the top area and the bottom area were both variables.

Experimental Investigation of Flow Instabilities in a Laminar Separation Bubble

The present paper reports the results of a detailed experimental study aimed at investigating the dynamics of a laminar separation bubble, from the origin of separation up to the breakdown to turbulence of the large scale co- herent structures generated as a consequence of the Kelvin-Helmholtz instability process. Measurements have been performed along a fiat plate installed within a double contoured test section, designed to produce an adverse pressure gradient typical of Ultra-High-Lift turbine blade profiles, which induces the formation of a laminar separation bubble at low Reynolds number condition. Measurements have been carried out by means of comple- mentary techniques： hot-wire （HW） anemometry, Laser Doppler Velocirnetry （LDV） and Particle Image Veloci- metry （PIV）. The high accuracy 2-dimensional LDV results allow investigating reverse flow magnitude and both Reynolds normal and shear stress distributions along the separated flow region, while the high frequency response of the HW anemometer allows analyzing the amplification process of flow oscillations induced by instability mechanisms. PIV results complement the flow field analysis providing information on the generation and evolu- tion of the large scale coherent structures shed as a consequence of the separated shear layer roll-up, through in- stantaneous velocity vector maps. The simultaneous analysis of the data obtained by means of the different meas- uring techniques allows an in depth view of the instability mechanisms involved in the transition/reattachrnent processes of the separated shear layer.

Detached-eddy simulations and analyses on new vortical flows over a 76/40° double delta wing

Numerical simulations were performed on the massively separated flows of a 76/40° double delta wing using detached-eddy simulation(DES).A new type of cross-flow vortex is suggested.A vortex was initially generated near the junction of the strake and wing,which then moved towards the wing tip at certain wavelength and speed.Analyses were made in detail on the mechanism of the generation of the cross-flow vortex,that is,the inviscid cross-flow instability which differs from that of the swept blunt wing.Cross-section topology of the cross-flow vortex is also investigated,and the wavelength of the vortex array and the characteristic frequency are given.The analyses showed that the cross-flow vortices have an influence on the pressure distribution,which can cause a 10%-20% deviation from the averaged distribution.

Control of the Asymmetric Flow in Rocket Nozzles

In some rocket nozzle flows, the existence of the transition from FSS to RSS and the occurrence of asymmetric flow are known in previous researches. As a result, the transition causes excessive side-loads that may damage the nozzle. Thus, it is important to investigate the method in order to control the asymmetric flow separation. In the present study, the relationship between the asymmetric separation and the rate of change of the pressure ratio with time was investigated from the point of view of the transition from FSS to RSS in the supersonic nozzle experimentally. Further, change of the flow separation by using step and cavity, and the possibility of the control was demonstrated. As a result, it was shown that the method using a cavity was effective for the control of the separation pattern.

Numerical Investigation of Pressure Distribution in a Low Specific Speed Centrifugal Pump

To study the pressure distribution of the volute casing, front casing and back casing in a prototype centrifugal pump, the pressure experiments and numerical simulations are carried out at six working conditions in this paper. The experimental results shows that the asymmetry of static pressure distribution on volute casing and front cavity is caused by the tongue of the volute and it may result in high radial and axial resultant force which can cause vibration and noise in the centrifugal pump. With the increasing of flow rote, the asymmetry of static pressure distribution and the magnitude of static pressure values reduce. The numerical results indicate that the pressure fluctuation near the tongue is strongest and it becomes slighter at point away from the tongue. With the increasing of flow rote, the local high=pressure region in impeller passage reduces and the flow becomes smoother accordingly, whereas the fluid speed becomes much higher which may cause further flow losses. The results predicted by numcrical simulation are in coincident with the experimental ones. It shows that the turbulence model for simulating the flow field in centrifugal pumps is feasible.