Numerical Investigation of Aerofoil Cascade and Tandem Cascade Using Vortex Panel Method

Panel methods are the numerical schemes for solving linear, inviscid, irrotational flow fields about arbitrary bodies at subsonic free-stream Mach numbers. The basic procedure is to discretize the body in terms of singularity distribution on the body surface then satisfy the necessary boundary conditions. It helps to determine the resulting distribution of singularity on the surface, and there by obtaining fluid dynamic properties of the flow. This project work describes a method for simulating, the potential flow field about the arbitrary two-dimensional bodies using MATLAB program. Even though singularities can be used as sources, doublets, or vortices, at this point the panel method uses the vortex element because it is talented to model both lifting forces and pressures. The numerical codes developed for this purpose computes the circulation, flow velocities, coefficient of lift and coefficient of pressure distribution over various geometries along with the streamline of corresponding bodies. Similarly the flow analysis is done for the same two dimensional bodies using FLUENT flow simulation tool and the results have been compared. The advantages of this numerical scheme over the conventional flow analysis are also presented in terms of reliable flow field data

Numerical Simulation of Projectile Impact on Mild Steel ArmourPlates using LS-DYNA: Part I: Validation

The paper describes  the simulation of impact of jacketed projectiles on steel armour plates usingexplicit finite element analysis as implemented in LS-DYNA. Validation of numerical modelling includesa comprehensive mesh convergence study leading to insights not previously reported in literature,using shell, solid, and axisymmetric elements for representing target plates. It is shown for a numberof cases that with a proper choice of contact algorithm, element size, and strain rate-dependent materialproperties, computed projectile residual velocities can match closely with corresponding test-basedvalues. The modelling requirements are arrived at by correlating against published test residual velocities1for variants of mild steel plates (designated as MS1, MS2 and MS3) of different thicknesses at impactvelocities in the range of ~820-870 m/s. Using the validated numerical procedure, a number of parametricstudies such as the effect of projectile shape and geometric aspect ratios as well as plate thickness onresidual velocity have been carried out and presented in Part II of the current paper

Numerical Investigation of Aerofoil Cascade and Tandem Cascade Using Vortex Panel Method

Panel methods are the numerical schemes for solving linear, inviscid, irrotational flow fields about arbitrary bodies at subsonic free-stream Mach numbers. The basic procedure is to discretize the body in terms of singularity distribution on the body surface then satisfy the necessary boundary conditions. It helps to determine the resulting distribution of singularity on the surface, and there by obtaining fluid dynamic properties of the flow. This project work describes a method for simulating, the potential flow field about the arbitrary two-dimensional bodies using MATLAB program. Even though singularities can be used as sources, doublets, or vortices, at this point the panel method uses the vortex element because it is talented to model both lifting forces and pressures. The numerical codes developed for this purpose computes the circulation, flow velocities, coefficient of lift and coefficient of pressure distribution over various geometries along with the streamline of corresponding bodies. Similarly the flow analysis is done for the same two dimensional bodies using FLUENT flow simulation tool and the results have been compared. The advantages of this numerical scheme over the conventional flow analysis are also presented in terms of reliable flow field data

Clinico-pathological association of delineated miRNAs in uveal melanoma with monosomy 3/Disomy 3 chromosomal aberrations

PURPOSE: To correlate the differentially expressed miRNAs with clinico-pathological features in uveal melanoma (UM) tumors harbouring chromosomal 3 aberrations among South Asian Indian cohort. METHODS: Based on chromosomal 3 aberration, UM (n = 86) were grouped into monosomy 3 (M3; n = 51) and disomy 3 (D3; n = 35) by chromogenic in-situ hybridisation (CISH). The clinico-pathological features were recorded. miRNA profiling was performed in formalin fixed paraffin embedded (FFPE) UM samples (n = 6) using Agilent, Human miRNA microarray, 8x15KV3 arrays. The association between miRNAs and clinico-pathological features were studied using univariate and multivariate analysis. miRNA-gene targets were predicted using Target-scan and MiRanda database. Significantly dys-regulated miRNAs were validated in FFPE UM (n = 86) and mRNAs were validated in frozen UM (n = 10) by qRT-PCR. Metastasis free-survival and miRNA expressions were analysed by Kaplen-Meier analysis in UM tissues (n = 52). RESULTS: Unsupervised analysis revealed 585 differentially expressed miRNAs while supervised analysis demonstrated 82 miRNAs (FDR; Q = 0.0). Differential expression of 8 miRNAs: miR-214, miR-149*, miR-143, miR-146b, miR-199a, let7b, miR-1238 and miR-134 were studied. Gene target prediction revealed SMAD4, WISP1, HIPK1, HDAC8 and C-KIT as the post-transcriptional regulators of miR-146b, miR-199a, miR-1238 and miR-134. Five miRNAs (miR-214, miR146b, miR-143, miR-199a and miR-134) were found to be differentially expressed in M3/ D3 UM tumors. In UM patients with liver metastasis, miR-149* and miR-134 expressions were strongly correlated. CONCLUSION: UM can be stratified using miRNAs from FFPE sections. miRNAs predicting liver metastasis and survival have been identified. Mechanistic linkage of de-regulated miRNA/mRNA expressions provide new insights on their role in UM progression and aggressiveness