NUMERICAL SIMULATION OF THE INTERACTION OF A TRANSVERSE JET WITH SUPERSONIC FLOW USING DIFFERENT TURBULENCE MODELS

AbstractA direct numerical simulation (DNS) of the incompressible flow around a rectangular cylinder with chord-to-thickness ratio 5:1 (also known as the BARC benchmark) is presented. The work replicates the first DNS of this kind recently presented by Cimarelli et al. (J Wind Eng Ind Aerodyn 174:39–495, 2018), and intends to contribute to a solid numerical benchmark, albeit at a relatively low value of the Reynolds number. The study differentiates from previous work by using an in-house finite-differences solver instead of the finite-volumes toolbox OpenFOAM, and by employing finer spatial discretization and longer temporal average. The main features of the flow are described, and quantitative differences with the existing results are highlighted. The complete set of terms appearing in the budget equation for the components of the Reynolds stress tensor is provided for the first time. The different regions of the flow where production, redistribution and dissipation of each component take place are identified, and the anisotropic and inhomogeneous nature of the flow is discussed. Such information is valuable for the verification and fine-tuning of turbulence models in this complex separating and reattaching flow.

Download Full-text

Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave

Shock Waves ◽

10.1007/s00193-012-0384-9 ◽

2012 ◽

Vol 22 (6) ◽

pp. 533-545 ◽

Cited By ~ 7

Author(s):

H. Yamauchi ◽

B. Choi ◽

K. Takae ◽

T. Kouchi ◽

G. Masuya

Keyword(s):

Shock Wave ◽

Supersonic Flow ◽

Transverse Jet

Download Full-text

Computational study of unsteady gas flow in the combustion chamber of a ramjet engine with heat transfer

Вычислительные технологии ◽

10.25743/ict.2020.25.6.003 ◽

2021 ◽

pp. 50-61

Author(s):

Надежда Петровна Скибина

Keyword(s):

Heat Transfer ◽

Numerical Simulation ◽

Supersonic Flow ◽

Combustion Chamber ◽

Gas Flow ◽

Stokes Equations ◽

Heat Conducting ◽

Measuring Device ◽

Ramjet Engine ◽

Mach Numbers

Проведено численное исследование нестационарного турбулентного сверхзвукового течения в камере сгорания прямоточного воздушно-реактивного двигателя. Описана методика экспериментального измерения температуры на стенке осесимметричного канала в камере сгорания двигателя. Математическое моделирование обтекания исследуемой модели двигателя проводилось для скоростей набегающего потока M = 5 ... 7. Начальные и граничные условия задачи соответствовали реальному аэродинамическому эксперименту. Проанализированы результаты численного расчета. Рассмотрено изменение распределения температуры вдоль стенки канала с течением времени. Проведена оценка согласованности полученных экспериментальных данных с результатами математического моделирования. Purpose. The aim of this study is a numerical simulation of unsteady supersonic gas flow in a working path of ramjet engine under conditions identical to aerodynamic tests. Free stream velocity corresponding to Mach numbers M=5 ... 7 are considered. Methodology. Presented study addresses the methods of physical and numerical simulation. The probing device for thermometric that allows to recording the temperature values along the wall of internal duct was proposed. To describe the motion of a viscous heat-conducting gas the unsteady Reynolds averaged Navier - Stokes equations are considered. The flow turbulence is accounted by the modified SST model. The problem was solved in ANSYS Fluent using finite-volume method. The initial and boundary conditions for unsteady calculation are set according to conditions of real aerodynamic tests. The coupled heat transfer for supersonic flow and elements of ramjet engine model are realized by setting of thermophysical properties of materials. The reliability testing of numerical simulation has been made to compare the results of calculations and the data of thermometric experimental tests. Findings. Numerical simulation of aerodynamic tests for ramjet engine was carried out. The agreement between the results of numerical calculations and experimental measurements for the velocity in the channel under consideration was obtained; the error was shown to be 2%. The temperature values were obtained in the area of contact of the supersonic flow with the surface of the measuring device for the external incident flow velocities for Mach numbers M = 5 ... 7. The process of heating the material in the channel that simulated the section of the engine combustion chamber was analyzed. The temperature distribution was studied depending on the position of the material layer under consideration relative to the contact zone with the flow. Value. In the course of the work, the fields of flow around the model of a ramjet engine were obtained, including the region of supersonic flow in the inner part of axisymmetric channel. The analysis of the temperature fields showed that to improve the quality of the results, it is necessary to take into account the depth of the calorimetric sensor. The obtained results will be used to estimate the time of interaction of the supersonic flow with the fuel surface required to reach the combustion temperature.

Download Full-text

Mixing of a Sonic Transverse Jet Injected into a Supersonic Flow

AIAA Journal ◽

10.2514/2.984 ◽

2000 ◽

Vol 38 (3) ◽

pp. 470-479 ◽

Cited By ~ 118

Author(s):

Wayne M. VanLerberghe ◽

Juan G. Santiago ◽

J. Craig Dutton ◽

Robert P. Lucht

Keyword(s):

Supersonic Flow ◽

Transverse Jet

Download Full-text

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.

Download Full-text