Modules identification in gene positive networks of hepatocellular carcinoma using pearson agglomerative method and Pearson cohesion coupling modularity

In this study, a gene positive network is proposed based on a weighted undirected graph, where the weight represents the positive correlation of the genes. A Pearson agglomerative clustering algorithm is employed to build a clustering tree, where dotted lines cut the tree from bottom to top leading to a number of subsets of the modules. In order to achieve better module partitions, the Pearson correlation coefficient modularity is addressed to seek optimal module decomposition by selecting an optimal threshold value. For the liver cancer gene network under study, we obtain a strong threshold value at 0.67302, and a very strong correlation threshold at 0.80086. On the basis of these threshold values, fourteen strong modules and thirteen very strong modules are obtained respectively. A certain degree of correspondence between the two types of modules is addressed as well. Finally, the biological significance of the two types of modules is analyzed and explained, which shows that these modules are closely related to the proliferation and metastasis of liver cancer. This discovery of the new modules may provide new clues and ideas for liver cancer treatment

Aerodynamics of F1 car side mirror

This study investigates the aerodynamic performance of a Formula 1 carrear view side mirror when the location of its glass is varied inside its frame. Bothexperimental and computational studies have been carried out for a simplifiedtwo-dimensional model of a typical Formula 1 mirror at different Reynoldsnumbers. Experimental results showed strong correlation between the mirror’sglass location and its drag over all investigated Reynolds number range of1.1 × 105 to 2.6 × 105 – as the mirror’s glass is located further inside its frame areduction in the drag is achieved with a maximum of 10%-11%. No change is foundin the mirror’s vortex shedding frequency at all investigated Reynolds numberswhich implies no structural impact of this modification. However thecomputational results obtained using Fluent failed to predict the changes in flowcharacteristics and drag caused by the proposed modification, more calculationsare needed using higher order numerical methods should be performed toinvestigate this phenomenon further to confirm the experimental findings

Multiangle social network recommendation algorithms and similarity network evaluation

Multiangle social network recommendation algorithms (MSN) and a new assessmentmethod, called similarity network evaluation (SNE), are both proposed. From the viewpoint of six dimensions, the MSN are classified into six algorithms, including user-based algorithmfromresource point (UBR), user-based algorithmfromtag point (UBT), resource-based algorithm fromtag point (RBT), resource-based algorithm from user point (RBU), tag-based algorithm from resource point (TBR), and tag-based algorithm from user point (TBU). Compared with the traditional recall/precision (RP) method, the SNE is more simple, effective, and visualized. The simulation results show that TBR and UBR are the best algorithms, RBU and TBU are the worst ones, and UBT and RBT are in the medium levels

Analysis of flow and aerodynamic noise behaviour of a simplified high-speed train bogie inside the bogie cavity

Aerodynamic noise becomes significant for high-speed trains but its prediction in an industrial context is difficult. The flow and aerodynamic noise behaviour of a simplified high-speed train bogie at scale 1:10 are studied here through numerical simulations. The bogie is situated in the bogie cavity and cases without and with a fairing are considered, allowing the shielding effect of the bogie fairing on sound generation and radiation to be investigated. A two-stage hybrid method combining computational fluid dynamics and acoustic analogy is applied. The near-field unsteady flow is obtained by solving the unsteady three-dimensional Navier-Stokes equations numerically using delayed detached-eddy simulation and the data are utilized to predict far-field noise signals based on the Ffowcs Williams-Hawkings acoustic analogy. Results show that when the bogie is located inside the bogie cavity, the shear layer developed from the cavity leading edge interacts strongly with the flow separated from the bogie upstream components and the cavity wall. Therefore, a highly turbulent flow is generated within the bogie cavity due to flow impingement and recirculation within the cavity. It is found that, for noise calculated from the bogie surface sources of both cases, the directivity exhibits a lateral dipole pattern with dominant radiation in the axial direction. Compared with the no fairing case, the noise level is about 1 dB higher in the bogie symmetry plane along the axle mid-span for the fairing case where a stronger flow interaction is produced around the bogie central region. Moreover, the noise radiated to the trackside is predicted based on a permeable integration surface close to the bogie and parallel to the carbody side wall. The results show that the bogie fairing is effective in reducing the noise levels in most of the frequency range due to its shielding effect and a noise reduction around 3 dB is achieved for the current model case by mounting a fairing in the bogie area

Large-eddy simulation of the interaction of a jet with a wing

This paper presents progresses made on aircraft installation effects using numerical methods under WP 3.2 of SYMPHONY, a project supported by Technology Strategy Board, UK. Large-eddy simulations (LES) were performed for turbulent flow around a wing under the influence from engine jet flow by solving the compressible Navier-Stokes equations using an in-horse high-order finite difference code. Simulations were performed for jet under both a clean wing and the wing at high-lift configuration. Installation effects on both the jet and the wing are analysed by comparing with LES results performed for three baseline cases: jet along, clean wing along and the wing in high-lift configuration. It is found that the flow is two-dimensional near the leading edge of the wing. Further down-stream three-dimensional flow features are developed. Interaction with vortical jet stream accelerates developments of the flow underneath the wing. Stronger turbulent structures are seen within the jet shear layer near the wing and their interaction with the wing causes surface pressure fluctuations, which results in increased radiated noise. Interaction with the jet causes a reduction in lift for the clean wing, however the contribution from the flap is increased when the wing is in high-lift configuration. For the current geometry the jet stream does not hit the clean wing, and it is shifted towards the wing by a small angle (one degree) due to low pressure region under the wing. When the ap is deployed, jet stream hits the flap and is deflected away from the wing

Sound radiation in turbulent channel flows

Lighthill’s acoustic analogy is formulated for turbulent channel flow with pressure as the acoustic variable, and integrated over the channel width to produce a two-dimensional inhomogeneous wave equation. The equivalent sources consist of a dipole distribution related to the sum of the viscous shear stresses on the two walls, together with monopole and quadrupole distributions related to the unsteady turbulent dissipation and Reynolds stresses respectively. Using a rigid-boundary Green function, an expression is found for the power spectrum of the far-field pressure radiated per unit channel area. Direct numerical simulations (DNS) of turbulent plane Poiseuille and Couette flow have been performed in large computational domains in order to obtain good resolution of the low-wavenumber source behaviour. Analysis of the DNS databases for all sound radiation sources shows that their wavenumber–frequency spectra have non-zero limits at low wavenumber. The sound power per unit channel area radiated by the dipole distribution is proportional to Mach number squared, while the monopole and quadrupole contributions are proportional to the fourth power of Mach number. Below a particular Mach number determined by the frequency and radiation direction, the dipole radiation due to the wall shear stress dominates the far field. The quadrupole takes over at Mach numbers above about 0.1, while the monopole is always the smallest term. The resultant acoustic field at any point in the channel consists of a statistically diffuse assembly of plane waves, with spectrum limited by damping to a value that is independent of Mach number in the low-M limit