Assessment of flow characteristics around twin rudder with various gaps using PIV analysis in uniform flow

This is a report on an investigation of the flow characteristics of a bluff body cut from a circular cylinder. The volume removed from the cylinder is equal to d/2(1 − cos θs), where d and θs are the diameter and the angular position (in the case of a circular cylinder, θs, = 0 deg), respectively. θs, ranged from 0 deg to 72.5 deg and Re (based on d and the upstream uniform flow velocity U∞) from 2.0 × 104 to 3.5 × 104. It is found that a singular flow around the cylinder occurs at around θs = 53 deg when Re > 2.5 × 104, and the base pressure coefficient (−Cpb,) and the drag coefficient CD take small values compared with those for otherθs.

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A Computational Study on the Effect of Angles of Attack on a Double-Cone Type Supersonic Inlet With Bleeding System

Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Education; Electric Power; Manufacturing Materials and Metallurgy ◽

10.1115/gt2010-23221 ◽

2010 ◽

Cited By ~ 1

Author(s):

Kyung Jin Ryu ◽

Seol Lim ◽

Sang Dug Kim ◽

Dong Joo Song

Keyword(s):

Boundary Layer ◽

Flow Field ◽

Computational Study ◽

Angle Of Attack ◽

Flow Characteristics ◽

Uniform Flow ◽

Double Cone ◽

Interface Plane ◽

Supersonic Inlet ◽

Cone Type

The flow characteristics on a supersonic inlet with bleeding system at various angles of attack are studied by using computational 3D turbulent flow analysis. A turbulent CSCM compressible upwind flux difference splitting Navier-Stokes method with k-w turbulence model is used to compute the inlet flowfields. MPICH-2.0 library and PC-cluster system are used to reduce computational times. Distortion and average of total pressure recovery at the AIP (aerodynamic interface plane) are used as evaluation criteria of inlet performance. The flow characteristics at zero of angle of attack of double-cone type supersonic inlet without and with bleeding system have been compared. Without bleeding system inlet with the strong SBLI (shock/boundary-layer interaction) induces slow flow recovery near the throat and produces very thick boundary layer downstream. But the bleeding system successfully removes the low energy flow from the boundary layer near the throat. As the angle of attack at the AIP because large, we can see more non-uniform flow field, and the non-uniform flow field is the major aggravating factor of inlet performance.

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Influence of the uniform flow on flow characteristics of tandem flapping wings

The Proceedings of Conference of Hokuriku-Shinetsu Branch ◽

10.1299/jsmehs.2018.55.f022 ◽

2018 ◽

Vol 2018.55 (0) ◽

pp. F022

Author(s):

Hirofumi TSUCHIDA ◽

Wataru YAMAZAKI

Keyword(s):

Flow Characteristics ◽

Uniform Flow ◽

Flapping Wings ◽

Tandem Flapping Wings

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Computation of uniform flow in open channels with flood plains

Canadian Journal of Civil Engineering ◽

10.1139/l91-017 ◽

1991 ◽

Vol 18 (1) ◽

pp. 149-155 ◽

Cited By ~ 2

Author(s):

Mysore G. Satish ◽

Yiping Guo ◽

Matiur Rahman

Keyword(s):

Eddy Viscosity ◽

Flow Characteristics ◽

Flood Plain ◽

Momentum Equation ◽

Uniform Flow ◽

Open Channels ◽

Two Dimensional ◽

Flood Plains ◽

The Past ◽

Averaged Model

For the computation of flow characteristics in open channels with flood plains, two-dimensional depth-averaged mathematical models have been used in the past. In the present study, the depth-averaged version of k–ε model including the term that accounts for the effect of the submerged vertical or steep boundaries on the flow characteristics in the momentum equation is presented. It is observed that inclusion of this term plays an important role in the distribution of the computed eddy viscosity in the interaction region between the flood plain and the main channel. The model is validated using the experimental data from earlier investigators. Key words: open channels, flood plains, two-dimensional depth-averaged model, uniform flow, k–ε turbulence model.

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