Numerical simulation of flows around deformed aircraft model in a wind tunnel

Large eddy simulation (LES) was made to solve the flow around two simplified CRH2 high speed trains passing by each other at the same speed base on the finite volume method and dynamic layering mesh method and three dimensional incompressible Navier-Stokes equations. Wind tunnel experimental method of resting train with relative flowing air and dynamic mesh method of moving train were compared. The results of numerical simulation show that the flow field structure around train is completely different between wind tunnel experiment and factual running. Two opposite moving couple of point source and point sink constitute the whole flow field structure during the high speed trains passing by each other. All of streamlines originate from point source (nose) and finish with the closer point sink (tail). The flow field structure around train is similar with different vehicle speed.

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The Influence of the Convective Terms Discretization Scheme on the Simulation Results of Architectural Numerical Wind Tunnel

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.204-208.4884 ◽

2012 ◽

Vol 204-208 ◽

pp. 4884-4887

Author(s):

Jian Feng Wu ◽

Cai Hua Wang ◽

Chang Li Song

Keyword(s):

Numerical Simulation ◽

Wind Tunnel ◽

Building Structures ◽

Discretization Scheme ◽

Shape Coefficient ◽

Fluent Software ◽

Actual Operation ◽

Simulation Results ◽

Load Shape ◽

Numerical Wind Tunnel Method

The numerical simulation of construction is to obtain the desired accuracy. It depends on the theoretical basis of the calculator and selection of the various important factors in the actual operation. For this problem, this paper adopting the current code for the design of building structures as the comparison standard, using the FLUENT software, taking the numerical simulation results of a high building’s wind load shape coefficient of for example, discussing the influence of four kinds of the convective terms discretization scheme, respectively the first-order upwind, the second order upwind , power law and Quadratic upwind interpolation for convective kinematics, on the simulation results of architectural numerical wind tunnel, provides the reference for the rational use of numerical wind tunnel method.

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Wind Tunnel Tests for Validation of Control Algorithms at High Angles of Attack Using Autonomous Aircraft Model Mounted in 3DOF Gimbals

AIAA Atmospheric Flight Mechanics Conference ◽

10.2514/6.2016-3106 ◽

2016 ◽

Author(s):

Dmitry I. Ignatyev ◽

Kamil G. Zaripov ◽

Maria E. Sidoryuk ◽

Konstantin A. Kolinko ◽

Alexander N. Khrabrov

Keyword(s):

Wind Tunnel ◽

Control Algorithms ◽

Wind Tunnel Tests ◽

Aircraft Model ◽

Autonomous Aircraft ◽

High Angles Of Attack

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Numerical Simulation of an Adaptive Wall in a Virtual Transonic Wind Tunnel

AIAA Journal ◽

10.2514/1.j055481 ◽

2017 ◽

Vol 55 (9) ◽

pp. 3214-3218 ◽

Cited By ~ 2

Author(s):

P. Weiand ◽

S. Michelis ◽

A. D. Gardner

Keyword(s):

Numerical Simulation ◽

Wind Tunnel ◽

Transonic Wind Tunnel

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Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests

Acta Polytechnica ◽

10.14311/530 ◽

2004 ◽

Vol 44 (2) ◽

Author(s):

A. V. Petrov ◽

Y. G. Stepanov ◽

M. V. Shmakov

Keyword(s):

Wind Tunnel ◽

Aerodynamic Characteristics ◽

Static Stability ◽

Light Transport ◽

Experimental Investigations ◽

Small Scale ◽

Left Hand ◽

Aircraft Model ◽

Turboprop Engine ◽

Control Surfaces

This report presents the results of experimental investigations into the interaction between the propellers (Ps) and the airframe of a twin-engine, twin-boom light transport aircraft with a Π-shaped tail. An analysis was performed of the forces and moments acting on the aircraft with rotating Ps. The main features of the methodology for windtunnel testing of an aircraft model with running Ps in TsAGI’s T-102 wind tunnel are outlined.The effect of 6-blade Ps slipstreams on the longitudinal and lateral aerodynamic characteristics as well as the effectiveness of the control surfaces was studied on the aircraft model in cruise and takeoff/landing configurations. The tests were conducted at flow velocities of V∞ = 20 to 50 m/s in the ranges of angles of attack α = -6 to 20 deg, sideslip angles of β = -16 to 16 deg and blade loading coefficient of B 0 to 2.8. For the aircraft of unusual layout studied, an increase in blowing intensity is shown to result in decreasing longitudinal static stability and significant asymmetry of the directional stability characteristics associated with the interaction between the Ps slipstreams of the same (left-hand) rotation and the empennage.

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The Problem of Airflow Around Building Clusters in Different Configurations

Archive of Mechanical Engineering ◽

10.1515/meceng-2017-0024 ◽

2017 ◽

Vol 64 (3) ◽

pp. 401-418 ◽

Cited By ~ 4

Author(s):

Mateusz Jędrzejewski ◽

Marta Poćwierz ◽

Katarzyna Zielonko-Jung

Keyword(s):

Numerical Simulation ◽

Wind Tunnel ◽

Pressure Measurement ◽

Turbulence Models ◽

Reynolds Stress Model ◽

Complex Model ◽

Stress Model ◽

Qualitative Information ◽

Pressure Coefficients ◽

Rsm Model

Abstract In the paper, the authors discuss the construction of a model of an exemplary urban layout. Numerical simulation has been performed by means of a commercial software Fluent using two different turbulence models: the popular k-ε realizable one, and the Reynolds Stress Model (RSM), which is still being developed. The former is a 2-equations model, while the latter – is a RSM model – that consists of 7 equations. The studies have shown that, in this specific case, a more complex model of turbulence is not necessary. The results obtained with this model are not more accurate than the ones obtained using the RKE model. The model, scale 1:400, was tested in a wind tunnel. The pressure measurement near buildings, oil visualization and scour technique were undertaken and described accordingly. Measurements gave the quantitative and qualitative information describing the nature of the flow. Finally, the data were compared with the results of the experiments performed. The pressure coefficients resulting from the experiment were compared with the coefficients obtained from the numerical simulation. At the same time velocity maps and streamlines obtained from the calculations were combined with the results of the oil visualisation and scour technique.

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