Numerical and Experimental Investigations of an ASME Venturi Flow in a Cross Flow

Size: px
Start display at page:

Download "Numerical and Experimental Investigations of an ASME Venturi Flow in a Cross Flow"

Transcription

1 40th Fluid Dynamics Conference and Exhibit 28 June - 1 July 2010, Chicago, Illinois AIAA Numerical and Experimental Investigations of an ASME Venturi Flow in a Cross Flow J. Bonifacio 1 and H.R. Rahai 2 Center for Energy and Environmental Research and Services (CEERS) California State University, Long Beach, Long Beach, Ca , USA R.H. Horstman 3 Environmental Control Systems, Boeing Commercial Airplane Group Seattle, WA, 98167, USA Numerical investigations of an ASME venturi flow into a cross flow were performed. The velocity ratios between the venturi flow and the free stream were 25, 50, and 75%. For the numerical investigations, two cases of the venturi with and without a tube extension have been investigated. The tube extension was approximately 4D (here D is the inner diameter of the venturi s outlet), connecting the venturi to the bottom surface of the numerical wind tunnel. A finite volume approach with the Wilcox K-ω turbulence model were used. Results for the numerical investigations indicate that when the venturi is flushed with the surface, there are flow separations within the venturi, near the outlet for 25% and 50% velocity ratios. However, at the higher momentum ratio, pressure recovery is sustained, flow separation has disappeared and flow characteristics are similar to a jet in cross flow. When the tube extension was added, at all velocity ratios, the pressure recovery was sustained and flow separation within the venture was not present and the characteristics of the flow were similar to the corresponding characteristics of a pipe jet in a cross flow. The paper also includes some experimental results at the venturi s outlet and in the near-field regions downstream of the jet in cross flow. Nomenclature D = venturi inner diameter at the outlet, cm x = axial direction, cm y = vertical direction, cm z = spanwise direction, cm C p = pressure coefficient U = axial mean velocity, m/sec. U = free stream mean velocity, m/sec. u = axial turbulent velocity, m/sec. TKE = turbulent kinetic energy I. Introduction The objective of the present investigations was to study flow characteristics of a venturi flow into a cross flow. The behavior of a venturi flow discharging into a free stream is very similar to the discharge of a turbulent jet in a cross flow. The turbulent jet in a cross-flow (JICF) has been the subject of extensive investigations due to its technological application involving mixing, dispersion and others such as vertical and short take-off and landing of aircraft. Margoson [1] has provided a review covering fifty years of research in JICF up to Recent studies [Examples are: Fric and Roshko [2], Smith and Mungal [3], Smith et al [4], Lozano et al [5], Eiff et al [6], and Eiff and Keffer [7]] have shown the existence of four main vortices namely: the jet shear layer vortices, the horseshoe vortices, the wake vortices, and the counter rotating vortex pairs. A major parameter used for characterizing the jet in a cross flow is the ratio of the jet momentum to the cross flow momentum, r. The wake vortices are observed for large velocity ratios while the counter-rotating vortex pair (CVP) is the dominant structure beyond the initial region. When r is less than one, for a jet flushed with a surface within the boundary layer, the jet momentum is not sufficient to penetrate the cross flow boundary layer. However, as r becomes greater than one, the jet has enough momentum to go beyond the cross flow boundary layer, before tilting in its direction and diffusing downstream. For an elevated jet, the jet momentum is not hindered by the cross-flow turbulent boundary layer and thus the initial interactions are just between the undisturbed cross flow and the jet. 1. Graduate Student, Research Assistant 2. Professor and Director 3. Associate Technical fellow Copyright 2010 by Bonifacio, Rahai, and Horstman. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.

2 The primary plane of circulation downstream of the JICF is the plane perpendicular to the streamwise flow. In the jet-wake area, previous investigations have shown the presence of jet-wake vortices that contributes to the counter-rotating vortex pair and originate from within the jet. For an elevated jet from a stack, the Karmen-like vortex structure in the stack-wake are locked to Karman-like vortex structures in the jet-wake, and they both contribute to the counter-rotating vortex pair [7]. Due to the unsteady nature of these vortices, the instantaneous concentration of the counter-rotating vortex pair is appeared to be asymmetrical and alternate with respect to the symmetric plane [4]. Flow through a venturi experiences an adverse pressure gradient, before discharging into cross flow. It has many engineering applications, including controlling the flow from a pressurized airplane cabin to the ambient. For an airplane at cruising condition, flow through the venturi is choked (sonic pressure) and the effective area is calculated from the cabin-ambient pressure ratio and the venturi flow rate, which is equal to the geometric area of the throat, multiplied by a discharge coefficient. However, when the airplane goes through ascent or descent, the pressure ratio is different and there might be a significant back pressure on the venturi which affects the location of the effective area and the flow rate. In these conditions, the venturi Mach number is significantly lower than the free stream Mach number and the flow characteristics through the venturi and the interaction region are not well understood. The flow behavior of the venturi could be divided into regions according to the flight profile. These regions in the direction of decreasing free stream Mach number from the sonic condition are: sonic flow condition where the venturi is chocked due to sufficient pressure ratio between the cabin and the ambient, the transition region where the Mach number of the venturi is higher than the free stream Mach number. In this condition, the pressure ratio between the cabin and the free stream is not sufficient to produce sonic flow and there could be flow separation within the diffuser which moves toward the exit and thus the effective area is not at sonic condition and is larger, the venturi diffuser recovery region where there is no separation within the venturi and the effective area is at the exit, and the interaction and the ram regions where the venturi Mach number is less than the free stream Mach number. These regions are associated with the airplane going through climb and descent conditions where the speed is less than the cruise speed. In these regions, there are possibilities of flow separation within the diffuser and the change in the effective throat area which could affect the venturi s mass flow rate. The objectives of the present investigations were to investigate these flow characteristics when the momentum ratio between the venturi flow and the free stream is less than one. A standard sonic ASME venturi was used for the present investigations. The focus of the investigations was on the flow characteristics within and at the outlet of the venturi and in the near field downstream. II.1. Computation II. CFD Analyses and Experiments The numerical investigations were performed using the Computational Fluid Dynamics (CFD) Software, Star CCM+ from CD-Adapco. Figure 1 shows the venturi with and without the extension, the flow domain models and the meshes used. The extension was a straight tube with the same diameter as the venturi s outlet diameter, D, with 4D in length. For the numerical investigations, the free stream velocity was at 54 m/s with the flow assumed to be fully developed and exit conditions pressure was kpa. The inlet for the plenum was fully developed and adjusted to allow a venturi exit velocity of 75%, 50% and 25% of the free stream velocity. For all calculations the standard (Wilcox) K-ω turbulence model was used. The fluid was air and was assumed to be ideal gas at isothermal condition. The solver chosen was segregated energy and the segregated fluid temp model was selected. The meshes were polyhedral with the following configurations: For Venturi Only: Number of Cells = , Number of Interior Faces = , and Number of Vertices = For Venturi with Extension: Number of Cells = , Number of Interior Faces = , and Number of Vertices =

3 Figure 1. The flow domain models with venturi with and without extensions. II.2. Experiments Figure 2 shows the experimental set-up and the venturi. The experiments were carried out in the low speed open-circuit blower wind tunnel of the CEERS which consists of six main components: the motor, blower, diffuser, settling chamber, contraction and test section. Air is driven through the tunnel by centrifugal blower which is a 3750 CFM backward airfoil type, powered by a 3 HP electric motor. The diffuser is a two-part diffuser expanding from 43.2X63.5 cm to 76.2X76.2 cm over a distance of 91.4 cm. Boundary layer control is provided by a screen with open area ratio of 62.4% paced across the flow at the middle of the diffuser. The diffuser section is followed by the settling chamber which has a hexagonal honeycomb (3.8 cm deep with 3.2 mm cells) and three screens with open area ratios of respectively 62.4%, 59.1% and 59.1%. Following the settling chamber is a 3-D contraction with a 10:1 area ratio over a distance of 91 cm. From the contraction, the flow is passed through another small two dimensional contraction which reduces the cross sectional area to 15.24X30.48 cm. The last contraction is followed by an all Plexiglas test section. The test section has the same cross section as the outlet of the contraction and is 90 cm long. The test section has static pressure taps on its large sides for monitoring the static pressure distribution. In the range of 3 to55 m/s, the mean velocity varies by less than 0.5% and at all speeds; the background intensity is less than 0.2%. The venturi system consisted of a direct motor connect centrifugal blower with digital speed controller, a flow conditioning chamber consisting of aluminum honeycomb and screens, a 6.25:1 axisymmetric contraction, followed by the connecting pipe to the venturi. For the experimental study, venturi was placed flushed with the bottom surface of the wind tunnel. The experiments were carried out at the wind tunnel free stream mean velocity of 34 m/sec. and the venturi mean flow of 25%, 50%, and 75% of the free stream mean velocity. The static pressure measurements were made on the diffuser wall upstream, and within the flow at the venturi s exit and in the near downstream interaction region. The profiles of the static pressure were obtained using a 1 mm diameter static pressure probe in conjunction with a, NIUSB-6009 data acquisition with LabView software. At each location 1024 samples/sec. were collected and averaged to get the static pressure difference between the measured location and the wind tunnel static pressure. The pressure coefficient was obtained by dividing the mean static pressure difference by the wind tunnel dynamic pressure. Further study of the flow characteristics was made using a single TSI hot wire probe in conjunction with a single channel of IFA-100 intelligent flow analyzer. Measurements were carried out at the mid-section plane across the venturi. At each location, a vertical profile of at least 50 points was obtained. For each point, 4096 samples were collected at a sample rate of 10,000 samples/sec., and analyzed using a NIUSB-6009 data acquisition board and Labview software. 3

4 Figure 2. Experimental Set-up (the venturi s dimensions are in inches) III. Results and Discussions Figures 3-7 show zoomed view of the contours of the mean velocity, static pressure, turbulent kinetic energy, vorticity and velocity vector for the venturi without extension, at the three velocity ratios of 25%, 50%, and 75%, along the axial mid-section plane. At 25% momentum ratio, the venturi flow into the cross flow is limited to an area very close to the wind tunnel surface and there are evidences of flow separation within the diffuser, near the outlet. There is limited static pressure gradient within the venturi, and increases in turbulent kinetic energy (TKE) and vorticity within the diffuser and near the outlet. There are areas of low velocity downstream, as the venturi flow penetrates into the cross flow. The velocity vector indicates a separation area within the diffuser. As the momentum ratio is increased, these features are more prominent, except for the region of flow separation within the venturi which is reduced. Figures 8-12 show similar results for the venturi with extension, There is no indication of flow separation within the diffuser at 25% and 50% velocity ratios and flow characteristics are very similar to characteristics of a round jet into a cross flow. There is increased pressure recovery within the extension tube and reduced TKE and vorticity generation at the jet outlet. With increased momentum ratio, the jet penetration into the cross flow is increased, and there are added TKE and vorticity within the extension tube. However, pressure recovery within the extension tube prevents flow separation and thus could speculate that the effective throat area of the venturi has not changed and the flow rate could be maintained. 4

5 Figure 3. Contours of axial mean velocity at the mid-plane for the venturi without extension at 25%, 50%, and 75% velocity ratios. Figure 4. Contours of static pressure at the mid-plane for the venturi without extension at 25%, 50%, and 75% velocity ratios. Figure 5. Contours of turbulent kinetic energy at the mid-plane for the venturi without extension at 25%, 50%, and 75% velocity ratios. Figure 6. Contours of vorticity at the mid-plane for the venturi without extension at 25%, 50%, and 75% velocity ratios. Figure 7. Contours of velocity vector at the mid-plane for the venturi without extension at 25%, 50%, and 75% velocity ratios. Figure 8. Contours of axial mean velocity at the mid-plane for the venturi with extension at 25%, 50%, and 75% velocity ratios. 5

6 Figure 9. Contours of static pressure at the mid-plane for the venturi with extension at 25%, 50%, and 75% velocity ratios. Figure 10. Contours of turbulent kinetic energy at the mid-plane for the venturi with extension at 25%, 50%, and 75% velocity ratios. Figure 11. Contours of vorticity at the mid-plane for the venturi with extension at 25%, 50%, and 75% velocity ratios. Figure 12. Contours of velocity vector at the mid-plane for the venturi with extension at 25%, 50%, and 75% velocity ratios. Figures 13 and 14 show variation of the static pressure coefficient in a plane perpendicular to the cross flow at x/d=1 and along the mid-plane in the cross flow direction for the venturi without the extension at no venturi flow, 25%, 50%, and 75% velocity ratios. For the plane at x/d=1, The static pressure is nearly uniform for the cross flow without the venturi flow and for the JICF cases, the increase in the static pressure coefficient is associated with the counter-rotating vortex pair which becomes more prominent with increasing the momentum ratio. At 50% and 75% momentun ratios, the Cp variations are significant with the highest Cp being at the core of the vortex pair. The axial pressure distribution at 25% monentum ratio show a low pressure region at the venturi s exit upstream which might be associated with flow separation and reattachment within the diffuser. At 50% momentum ratio, the static pressure is increased and is relatively uniform at the venturi s first half outlet which is an indication of the pressure recovery within the diffuser. However, the second half of the venturi downstream is experiemcing a non uniform static pressure which might be associated with aerodynamic ram. Figure 15 shows variation of the pressure coefficient along the diffuser wall. The static pressure taps starts at approximately 1.5 inch downstream of the venturi s throat and terminates at approximately the same distance before the diffuser exit. The x values are measured from the venturi s outlet toward the reduced cross sectional area. For the 25% momentum ratio, the pressure recovery is not significant, except near the outlet where there is a slight increase in the pressure recovery. This could be due to limited penetration of the venturi flow into the cross flow, and may result in semi-reservoir condition. 6

7 For 50% and 75% velocity ratios, there are significant pressure recovery, especially near the venturi outlet. For 50% pressure ratio, the increase starts at around 4 inches, while for the 75% momentum ratio, it is around 7 inches. In generall, the higher the momntum ratio, the higher the pentration of the venturi flow into the cross flow and thus the earlier start of the pressure recovery. (a) (b) (c) (d) Figure 13. Variation of the static pressure coefficient at x/d =1, for (a) no venturi flow, (b) 25% momentum ratio, (c) 50% momentum ratio, and (d) 75% momentum ratio. 7

8 (a) (b) (c ) (d) Figure 14. Axial variation of the static pressure coefficient Cp at the mid-plane for (a) no venturi flow, (b) 25% momentum ratio, (c) 50% momentum ratio, and (d) 75% momentum ratio % Momentume ratio 50% Momentum ratio 75% Momentum ratio 1.5 Cp X(inches) Figure 15. Variation of the pressure coefficient along the diffuser wall. Figures 16 and 17 show axial normalized mean velocity and turbulence intensity from hot wire measurements at the outlet of the venturi for different velocity ratios. For 25% ratio, there are areas of low velocity at the first half of the venturi outlet. As the velocity ratio increases, the high velocity region of the second half expands into the first half, reducing the low velocity region. The low velocity region is associated with the imposition of pressure by freestream flow and possible streaming of the free stream flow into the venturi. The turbulence intensity increases with expansion of the high velocity region due to higher velocity gradient and stretching of the flow in this region. 8

9 Figure 18 show power spectra of axial turbulent velocity along the mid-axial plane at x/d=5 and y/d = 1.2. With increasing the velocity ratio, there increases in energy at low frequency which corresponds to increases in large scale structures. This location corresponds to the mid-spanwise plane where the two counter-rotating vortices form where with increasing the velocity ratio, they become more pronounced. Energy of the small eddies seems to be unchanged. Figure 16. Axial mean velocity contours from hot wire measurements for (from left to right) 25%, 50%, and 75% mean velocity ratios. Figure 17. Axial turbulence intensity contours from hot wire measurements for (from left to right) 25%, 50%, and 75% mean velocity ratios. (a) (b) Figure 18. Power spectr of axial turbulent velocity, from left, for 25%, 50%, and 75% velocity ratios respectively, along the mid-axial plane at x/d=5 and y/d=1.2. (c ) IV. Conclusion Numerical and experimental investigations of an ASME venturi flow into a cross flow have been investigated. For the numerical investigation, two cases of the venturi flow with and without the addition of the extension tube into the cross flow were investigated, while the experimental investigations were limited to just the venturi flow into the cross flow. The investigations were performed for mean velocity ratios of 25%, 50%, and 75%. Here the free stream mean velocity was at 54 m/sec. for the numerical analyses and 34 m/sec. for the experimental investigations. The numerical investigations were performed using Reynolds-Averaged Navier-Stokes equation using the commercially available software (STAR CCM+) from CD-Adapco with Wilcox K-ω turbulence model. The experimental investigations were performed with a small static pressure probe and a single channel TSI hotwire anemometer. Results show that for the venturi without extension, at 25% velocity ratio, pressure recovery within the 9

10 venturi is small, except near the outlet which may limit uniform penetration of the venturi flow into the cross flow. With increasing the velocity ratio, pressure recovery is increased, resulting in higher penetration of the venturi flow into the cross flow. There are areas of very low velocity at the venturi outlet upstream, which might be due to impingement of the cross flow on the venturi flow, resulting in slow flow conditions. With increasing the velocity ratio, the low velocity region is reduced. While the mean flow characteristics downstream is very similar to the characteristics of a jet in cross flow, however, in the near interaction region between the venturi flow and the cross flow, there are non-uniformity due to the adverse pressure gradient within the venturi which may results in non-uniformity within the venturi and in the case of low velocity ratio, resulting in errors in estimating the actual flow rate. Acknowledgments Supports from the Boeing Company, Environmental Control Systems division, Seattle, Washington for the present investigations are gratefully acknowledged. The authors would also like to thank Mr. Ehsan Shamloo of CEERS, and Mr. Mike Fritz of Mechanical and Aerospace Engineering at CSULB for their technical supports.. References 1. Margason, R.J., 1993, Computational and Experimental Assessment of Jets in Cross Flow, AGARD, CP Fric, T.F, and Roshko, A., 1994, Vertical Structure in the Wake of a Transverse Jet, J. Fluid Mech., Vol. 279, pp Smith, S., Lozano, A., Mungal, M.G., and Hanson, R.K., 1993, Scalar Mixing in a Subsonic Jet in Cross- Flow, AGARD Jet in Cross Flow Symp., pp Winchester, UK. 4. Smith, S. and Mungal, M.G., 1998, Mixing Structure and Scaling of the Jet in Cross Flow, J. of Fluid Mechanics, Vol. 357, pp Lozano, A., Smith, S.H., Mungal, M.G., and Hanson, R.K., 1994, Concentration Measurements in a Transverse Jet by Planer Laser-Induced Fluorescence of Acetone, AIAA J., 32, Eiff, O.S., Kawall, J.G., and Keffer, J.F., 1995, Lock-in of Vortices in the Wake of an Elevated Round Turbulent Jet in a Cross Flow, Exp. In Fluids, 19, Eiff, O.S.and Keffer, J.F., 1997, On the Structures in the Near-Wake Region of an Elevated Turbulent Jet in a Cross Flow, J. Fluid Mech., vol. 333, pp Jones, W.P., and launder, B.E., 1972, The prediction of Laminarization with a Two-Equation Model of Turbulence, Int. J. of Heat and Mass Transfer, Vol. 15, pp Launder, B.E., and Sharma, B.I., 1974, Application of the Energy Dissipation Model of Turbulence to the Calculation of the Flow Near a Spinning Disc, Letter in heat and Mass Transfer, Vol. 1, No.2, pp Dewey, P.E. and Vick, A.R., 1955, An Investigation of the Discharge and Drag Characteristics of Auxiliary-Air Outlets Discharging into A Transonic Stream, NACA Technical Note

CHAPTER 4 CFD ANALYSIS OF THE MIXER

CHAPTER 4 CFD ANALYSIS OF THE MIXER 98 CHAPTER 4 CFD ANALYSIS OF THE MIXER This section presents CFD results for the venturi-jet mixer and compares the predicted mixing pattern with the present experimental results and correlation results

More information

NUMERICAL ANALYSIS OF THE EFFECTS OF WIND ON BUILDING STRUCTURES

NUMERICAL ANALYSIS OF THE EFFECTS OF WIND ON BUILDING STRUCTURES Vol. XX 2012 No. 4 28 34 J. ŠIMIČEK O. HUBOVÁ NUMERICAL ANALYSIS OF THE EFFECTS OF WIND ON BUILDING STRUCTURES Jozef ŠIMIČEK email: jozef.simicek@stuba.sk Research field: Statics and Dynamics Fluids mechanics

More information

Lecture 6 - Boundary Conditions. Applied Computational Fluid Dynamics

Lecture 6 - Boundary Conditions. Applied Computational Fluid Dynamics Lecture 6 - Boundary Conditions Applied Computational Fluid Dynamics Instructor: André Bakker http://www.bakker.org André Bakker (2002-2006) Fluent Inc. (2002) 1 Outline Overview. Inlet and outlet boundaries.

More information

CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation

CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation Page1 CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation ABSTRACT Alan Vincent E V P G Scholar, Nehru Institute of Engineering and Technology, Coimbatore Tamil Nadu A high

More information

A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic

A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic AiMT Advances in Military Technology Vol. 8, No. 1, June 2013 Aerodynamic Characteristics of Multi-Element Iced Airfoil CFD Simulation A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty

More information

Chapter 10. Flow Rate. Flow Rate. Flow Measurements. The velocity of the flow is described at any

Chapter 10. Flow Rate. Flow Rate. Flow Measurements. The velocity of the flow is described at any Chapter 10 Flow Measurements Material from Theory and Design for Mechanical Measurements; Figliola, Third Edition Flow Rate Flow rate can be expressed in terms of volume flow rate (volume/time) or mass

More information

ME 239: Rocket Propulsion. Over- and Under-expanded Nozzles and Nozzle Configurations. J. M. Meyers, PhD

ME 239: Rocket Propulsion. Over- and Under-expanded Nozzles and Nozzle Configurations. J. M. Meyers, PhD ME 239: Rocket Propulsion Over- and Under-expanded Nozzles and Nozzle Configurations J. M. Meyers, PhD 1 Over- and Underexpanded Nozzles Underexpanded Nozzle Discharges fluid at an exit pressure greater

More information

Keywords: Heat transfer enhancement; staggered arrangement; Triangular Prism, Reynolds Number. 1. Introduction

Keywords: Heat transfer enhancement; staggered arrangement; Triangular Prism, Reynolds Number. 1. Introduction Heat transfer augmentation in rectangular channel using four triangular prisms arrange in staggered manner Manoj Kumar 1, Sunil Dhingra 2, Gurjeet Singh 3 1 Student, 2,3 Assistant Professor 1.2 Department

More information

HEAT TRANSFER ANALYSIS IN A 3D SQUARE CHANNEL LAMINAR FLOW WITH USING BAFFLES 1 Vikram Bishnoi

HEAT TRANSFER ANALYSIS IN A 3D SQUARE CHANNEL LAMINAR FLOW WITH USING BAFFLES 1 Vikram Bishnoi HEAT TRANSFER ANALYSIS IN A 3D SQUARE CHANNEL LAMINAR FLOW WITH USING BAFFLES 1 Vikram Bishnoi 2 Rajesh Dudi 1 Scholar and 2 Assistant Professor,Department of Mechanical Engineering, OITM, Hisar (Haryana)

More information

COMPUTATIONAL FLOW MODEL OF WESTFALL'S 4000 OPEN CHANNEL MIXER 411527-1R1. By Kimbal A. Hall, PE. Submitted to: WESTFALL MANUFACTURING COMPANY

COMPUTATIONAL FLOW MODEL OF WESTFALL'S 4000 OPEN CHANNEL MIXER 411527-1R1. By Kimbal A. Hall, PE. Submitted to: WESTFALL MANUFACTURING COMPANY COMPUTATIONAL FLOW MODEL OF WESTFALL'S 4000 OPEN CHANNEL MIXER 411527-1R1 By Kimbal A. Hall, PE Submitted to: WESTFALL MANUFACTURING COMPANY FEBRUARY 2012 ALDEN RESEARCH LABORATORY, INC. 30 Shrewsbury

More information

INLET AND EXAUST NOZZLES Chap. 10 AIAA AIRCRAFT ENGINE DESIGN R01-07/11/2011

INLET AND EXAUST NOZZLES Chap. 10 AIAA AIRCRAFT ENGINE DESIGN R01-07/11/2011 MASTER OF SCIENCE IN AEROSPACE ENGINEERING PROPULSION AND COMBUSTION INLET AND EXAUST NOZZLES Chap. 10 AIAA AIRCRAFT ENGINE DESIGN R01-07/11/2011 LECTURE NOTES AVAILABLE ON https://www.ingegneriaindustriale.unisalento.it/scheda_docente/-/people/antonio.ficarella/materiale

More information

Numerical Simulation of the External Flow Field. Around a Bluff Car*

Numerical Simulation of the External Flow Field. Around a Bluff Car* Numerical Simulation of the External Flow Field Around a Bluff Car* Sun Yongling, Wu Guangqiang, Xieshuo Automotive Engineering Department Shanghai Tongji University Shanghai, China E-mail: wuqjuhyk@online.sh.cn

More information

Abaqus/CFD Sample Problems. Abaqus 6.10

Abaqus/CFD Sample Problems. Abaqus 6.10 Abaqus/CFD Sample Problems Abaqus 6.10 Contents 1. Oscillatory Laminar Plane Poiseuille Flow 2. Flow in Shear Driven Cavities 3. Buoyancy Driven Flow in Cavities 4. Turbulent Flow in a Rectangular Channel

More information

Keywords: CFD, heat turbomachinery, Compound Lean Nozzle, Controlled Flow Nozzle, efficiency.

Keywords: CFD, heat turbomachinery, Compound Lean Nozzle, Controlled Flow Nozzle, efficiency. CALCULATION OF FLOW CHARACTERISTICS IN HEAT TURBOMACHINERY TURBINE STAGE WITH DIFFERENT THREE DIMENSIONAL SHAPE OF THE STATOR BLADE WITH ANSYS CFX SOFTWARE A. Yangyozov *, R. Willinger ** * Department

More information

Averaging Pitot Tubes; Fact and Fiction

Averaging Pitot Tubes; Fact and Fiction Averaging Pitot Tubes; Fact and Fiction Abstract An experimental investigation has been undertaken to elucidate effects of averaging stagnation pressures on estimated velocities for pressure averaging

More information

Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD

Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD Universal Journal of Mechanical Engineering 1(4): 122-127, 2013 DOI: 10.13189/ujme.2013.010403 http://www.hrpub.org Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD Vibhor Baghel

More information

CO 2 41.2 MPa (abs) 20 C

CO 2 41.2 MPa (abs) 20 C comp_02 A CO 2 cartridge is used to propel a small rocket cart. Compressed CO 2, stored at a pressure of 41.2 MPa (abs) and a temperature of 20 C, is expanded through a smoothly contoured converging nozzle

More information

Dimensional Analysis

Dimensional Analysis Dimensional Analysis An Important Example from Fluid Mechanics: Viscous Shear Forces V d t / / / / / / / / / / / / / / / / / / / / / / / / / / / / / / / / / Ƭ = F/A = μ V/d More generally, the viscous

More information

Turbulence Modeling in CFD Simulation of Intake Manifold for a 4 Cylinder Engine

Turbulence Modeling in CFD Simulation of Intake Manifold for a 4 Cylinder Engine HEFAT2012 9 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 16 18 July 2012 Malta Turbulence Modeling in CFD Simulation of Intake Manifold for a 4 Cylinder Engine Dr MK

More information

Steady Flow: Laminar and Turbulent in an S-Bend

Steady Flow: Laminar and Turbulent in an S-Bend STAR-CCM+ User Guide 6663 Steady Flow: Laminar and Turbulent in an S-Bend This tutorial demonstrates the flow of an incompressible gas through an s-bend of constant diameter (2 cm), for both laminar and

More information

CFD Grows Up! Martin W. Liddament Ventilation, Energy and Environmental Technology (VEETECH Ltd) What is Computational Fluid Dynamics?

CFD Grows Up! Martin W. Liddament Ventilation, Energy and Environmental Technology (VEETECH Ltd) What is Computational Fluid Dynamics? CIBSE/ASHRAE Meeting CFD Grows Up! Martin W. Liddament Ventilation, Energy and Environmental Technology (VEETECH Ltd) 10 th December 2003 What is Computational Fluid Dynamics? CFD is a numerical means

More information

Using CFD to improve the design of a circulating water channel

Using CFD to improve the design of a circulating water channel 2-7 December 27 Using CFD to improve the design of a circulating water channel M.G. Pullinger and J.E. Sargison School of Engineering University of Tasmania, Hobart, TAS, 71 AUSTRALIA Abstract Computational

More information

AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL

AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL 14 th European Conference on Mixing Warszawa, 10-13 September 2012 AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL Joanna Karcz, Lukasz Kacperski

More information

Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412

Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412 , July 2-4, 2014, London, U.K. Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412 Arvind Prabhakar, Ayush Ohri Abstract Winglets are angled extensions or vertical projections

More information

SEPARATING DUST PARTICLES USING AN AERODYNAMIC DEDUSTER

SEPARATING DUST PARTICLES USING AN AERODYNAMIC DEDUSTER SEPARATING DUST PARTICLES USING AN AERODYNAMIC DEDUSTER DEVELOPMENT OF AN AERODYNAMIC DEDUSTER FOR LIVESTOCK BUILDINGS G.A. Zhao, Y. Zhang Summary Dust is among the major pollutants that have a detrimental

More information

FLUID FLOW STREAMLINE LAMINAR FLOW TURBULENT FLOW REYNOLDS NUMBER

FLUID FLOW STREAMLINE LAMINAR FLOW TURBULENT FLOW REYNOLDS NUMBER VISUAL PHYSICS School of Physics University of Sydney Australia FLUID FLOW STREAMLINE LAMINAR FLOW TURBULENT FLOW REYNOLDS NUMBER? What type of fluid flow is observed? The above pictures show how the effect

More information

Simulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640

Simulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Simulation at Aeronautics Test A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Questions How has the ability to do increasingly accurate modeling and

More information

Head Loss in Pipe Flow ME 123: Mechanical Engineering Laboratory II: Fluids

Head Loss in Pipe Flow ME 123: Mechanical Engineering Laboratory II: Fluids Head Loss in Pipe Flow ME 123: Mechanical Engineering Laboratory II: Fluids Dr. J. M. Meyers Dr. D. G. Fletcher Dr. Y. Dubief 1. Introduction Last lab you investigated flow loss in a pipe due to the roughness

More information

INTRODUCTION TO FLUID MECHANICS

INTRODUCTION TO FLUID MECHANICS INTRODUCTION TO FLUID MECHANICS SIXTH EDITION ROBERT W. FOX Purdue University ALAN T. MCDONALD Purdue University PHILIP J. PRITCHARD Manhattan College JOHN WILEY & SONS, INC. CONTENTS CHAPTER 1 INTRODUCTION

More information

The Influence of Aerodynamics on the Design of High-Performance Road Vehicles

The Influence of Aerodynamics on the Design of High-Performance Road Vehicles The Influence of Aerodynamics on the Design of High-Performance Road Vehicles Guido Buresti Department of Aerospace Engineering University of Pisa (Italy) 1 CONTENTS ELEMENTS OF AERODYNAMICS AERODYNAMICS

More information

TWO-DIMENSIONAL FINITE ELEMENT ANALYSIS OF FORCED CONVECTION FLOW AND HEAT TRANSFER IN A LAMINAR CHANNEL FLOW

TWO-DIMENSIONAL FINITE ELEMENT ANALYSIS OF FORCED CONVECTION FLOW AND HEAT TRANSFER IN A LAMINAR CHANNEL FLOW TWO-DIMENSIONAL FINITE ELEMENT ANALYSIS OF FORCED CONVECTION FLOW AND HEAT TRANSFER IN A LAMINAR CHANNEL FLOW Rajesh Khatri 1, 1 M.Tech Scholar, Department of Mechanical Engineering, S.A.T.I., vidisha

More information

Pushing the limits. Turbine simulation for next-generation turbochargers

Pushing the limits. Turbine simulation for next-generation turbochargers Pushing the limits Turbine simulation for next-generation turbochargers KWOK-KAI SO, BENT PHILLIPSEN, MAGNUS FISCHER Computational fluid dynamics (CFD) has matured and is now an indispensable tool for

More information

CFD Analysis of Swept and Leaned Transonic Compressor Rotor

CFD Analysis of Swept and Leaned Transonic Compressor Rotor CFD Analysis of Swept and Leaned Transonic Compressor Nivin Francis #1, J. Bruce Ralphin Rose *2 #1 Student, Department of Aeronautical Engineering& Regional Centre of Anna University Tirunelveli India

More information

Use of OpenFoam in a CFD analysis of a finger type slug catcher. Dynaflow Conference 2011 January 13 2011, Rotterdam, the Netherlands

Use of OpenFoam in a CFD analysis of a finger type slug catcher. Dynaflow Conference 2011 January 13 2011, Rotterdam, the Netherlands Use of OpenFoam in a CFD analysis of a finger type slug catcher Dynaflow Conference 2011 January 13 2011, Rotterdam, the Netherlands Agenda Project background Analytical analysis of two-phase flow regimes

More information

International Journal of ChemTech Research CODEN (USA): IJCRGG ISSN: 0974-4290 Vol.7, No.6, pp 2580-2587, 2014-2015

International Journal of ChemTech Research CODEN (USA): IJCRGG ISSN: 0974-4290 Vol.7, No.6, pp 2580-2587, 2014-2015 International Journal of ChemTech Research CODEN (USA): IJCRGG ISSN: 0974-4290 Vol.7, No.6, pp 2580-2587, 2014-2015 Performance Analysis of Heat Transfer and Effectiveness on Laminar Flow with Effect of

More information

Aerodynamics of Rotating Discs

Aerodynamics of Rotating Discs Proceedings of ICFD 10: Tenth International Congress of FluidofDynamics Proceedings ICFD 10: December 16-19, 2010, Stella Di MareTenth Sea Club Hotel, Ain Soukhna, Egypt International Congress of Red FluidSea,

More information

Numerical simulations of heat transfer in plane channel

Numerical simulations of heat transfer in plane channel Numerical simulations of heat transfer in plane channel flow Najla El Gharbi, Rafik Absi, Ahmed Benzaoui To cite this version: Najla El Gharbi, Rafik Absi, Ahmed Benzaoui. Numerical simulations of heat

More information

Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT

Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT Adam Dziubiński CFD group IoA FLUENT Content Fluent CFD software 1. Short description of main features of Fluent 2. Examples of usage in CESAR Analysis of flow around an airfoil with a flap: VZLU + ILL4xx

More information

CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS

CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS K.Harish Kumar 1, CH.Kiran Kumar 2, T.Naveen Kumar 3 1 M.Tech Thermal Engineering, Sanketika Institute of Technology & Management,

More information

2013 Code_Saturne User Group Meeting. EDF R&D Chatou, France. 9 th April 2013

2013 Code_Saturne User Group Meeting. EDF R&D Chatou, France. 9 th April 2013 2013 Code_Saturne User Group Meeting EDF R&D Chatou, France 9 th April 2013 Thermal Comfort in Train Passenger Cars Contact For further information please contact: Brian ANGEL Director RENUDA France brian.angel@renuda.com

More information

Flow Physics Analysis of Three-Bucket Helical Savonius Rotor at Twist Angle Using CFD

Flow Physics Analysis of Three-Bucket Helical Savonius Rotor at Twist Angle Using CFD Vol.3, Issue.2, March-April. 2013 pp-739-746 ISSN: 2249-6645 Flow Physics Analysis of Three-Bucket Helical Savonius Rotor at Twist Angle Using CFD Pinku Debnath, 1 Rajat Gupta 2 12 Mechanical Engineering,

More information

HEAT TRANSFER ENHANCEMENT IN FIN AND TUBE HEAT EXCHANGER - A REVIEW

HEAT TRANSFER ENHANCEMENT IN FIN AND TUBE HEAT EXCHANGER - A REVIEW HEAT TRANSFER ENHANCEMENT IN FIN AND TUBE HEAT EXCHANGER - A REVIEW Praful Date 1 and V. W. Khond 2 1 M. Tech. Heat Power Engineering, G.H Raisoni College of Engineering, Nagpur, Maharashtra, India 2 Department

More information

Basics of vehicle aerodynamics

Basics of vehicle aerodynamics Basics of vehicle aerodynamics Prof. Tamás Lajos Budapest University of Technology and Economics Department of Fluid Mechanics University of Rome La Sapienza 2002 Influence of flow characteristics on the

More information

Appendix 4-C. Open Channel Theory

Appendix 4-C. Open Channel Theory 4-C-1 Appendix 4-C Open Channel Theory 4-C-2 Appendix 4.C - Table of Contents 4.C.1 Open Channel Flow Theory 4-C-3 4.C.2 Concepts 4-C-3 4.C.2.1 Specific Energy 4-C-3 4.C.2.2 Velocity Distribution Coefficient

More information

CFD SIMULATION OF SDHW STORAGE TANK WITH AND WITHOUT HEATER

CFD SIMULATION OF SDHW STORAGE TANK WITH AND WITHOUT HEATER International Journal of Advancements in Research & Technology, Volume 1, Issue2, July-2012 1 CFD SIMULATION OF SDHW STORAGE TANK WITH AND WITHOUT HEATER ABSTRACT (1) Mr. Mainak Bhaumik M.E. (Thermal Engg.)

More information

Comparison of Heat Transfer between a Helical and Straight Tube Heat Exchanger

Comparison of Heat Transfer between a Helical and Straight Tube Heat Exchanger International Journal of Engineering Research and Technology. ISSN 0974-3154 Volume 6, Number 1 (2013), pp. 33-40 International Research Publication House http://www.irphouse.com Comparison of Heat Transfer

More information

Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design

Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Background Introduction ATS Company Background New and

More information

The calculation of train slipstreams using Large-Eddy Simulation techniques

The calculation of train slipstreams using Large-Eddy Simulation techniques The calculation of train slipstreams using Large-Eddy Simulation techniques Abstract Hassan Hemida, Chris Baker Birmingham Centre for Railway Research and Education, School of Civil Engineering, University

More information

(NASA-CR-199637) FLOW N96-13156 CHARACTERISTICS IN BOUNDARY LAYER BLEED SLOTS WITH PLENUM (Cincinnati Univ.) 10 p Unclas 63/34 0072808

(NASA-CR-199637) FLOW N96-13156 CHARACTERISTICS IN BOUNDARY LAYER BLEED SLOTS WITH PLENUM (Cincinnati Univ.) 10 p Unclas 63/34 0072808 (NASA-CR-199637) FLOW N96-13156 CHARACTERISTICS IN BOUNDARY LAYER BLEED SLOTS WITH PLENUM (Cincinnati Univ.) 10 p Unclas 63/34 0072808 NASA-CR-199637 AIAA 95-0033 FLOW CHARACTERISTICS IN BOUNDARY LAYER

More information

A Comparison of Analytical and Finite Element Solutions for Laminar Flow Conditions Near Gaussian Constrictions

A Comparison of Analytical and Finite Element Solutions for Laminar Flow Conditions Near Gaussian Constrictions A Comparison of Analytical and Finite Element Solutions for Laminar Flow Conditions Near Gaussian Constrictions by Laura Noelle Race An Engineering Project Submitted to the Graduate Faculty of Rensselaer

More information

Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids

Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids Dr. J. M. Meyers Dr. D. G. Fletcher Dr. Y. Dubief 1. Introduction In this lab the characteristics of airfoil lift, drag,

More information

Performance Comparison of a Vertical Axis Wind Turbine using Commercial and Open Source Computational Fluid Dynamics based Codes

Performance Comparison of a Vertical Axis Wind Turbine using Commercial and Open Source Computational Fluid Dynamics based Codes Performance Comparison of a Vertical Axis Wind Turbine using Commercial and Open Source Computational Fluid Dynamics based Codes Taimoor Asim 1, Rakesh Mishra 1, Sree Nirjhor Kaysthagir 1, Ghada Aboufares

More information

EXPERIMENTAL ANALYSIS OF HEAT TRANSFER ENHANCEMENT IN A CIRCULAR TUBE WITH DIFFERENT TWIST RATIO OF TWISTED TAPE INSERTS

EXPERIMENTAL ANALYSIS OF HEAT TRANSFER ENHANCEMENT IN A CIRCULAR TUBE WITH DIFFERENT TWIST RATIO OF TWISTED TAPE INSERTS INTERNATIONAL JOURNAL OF HEAT AND TECHNOLOGY Vol.33 (2015), No.3, pp.158-162 http://dx.doi.org/10.18280/ijht.330324 EXPERIMENTAL ANALYSIS OF HEAT TRANSFER ENHANCEMENT IN A CIRCULAR TUBE WITH DIFFERENT

More information

CFD Analysis of Automotive Ventilated Disc Brake Rotor

CFD Analysis of Automotive Ventilated Disc Brake Rotor RESEARCH ARTICLE OPEN ACCESS CFD Analysis of Automotive Ventilated Disc Brake Rotor Amol V. More*, Prof.Sivakumar R. ** *(M.Tech CAD/CAM, VIT University, Chennai) ** (School of Mechanical and Building

More information

Chapter 5 MASS, BERNOULLI AND ENERGY EQUATIONS

Chapter 5 MASS, BERNOULLI AND ENERGY EQUATIONS Fluid Mechanics: Fundamentals and Applications, 2nd Edition Yunus A. Cengel, John M. Cimbala McGraw-Hill, 2010 Chapter 5 MASS, BERNOULLI AND ENERGY EQUATIONS Lecture slides by Hasan Hacışevki Copyright

More information

CFD ANALYSES OF FLUID FLOW AND HEAT TRANSFER IN PATTERNED ROLL-BONDED ALUMINIUM PLATE RADIATORS

CFD ANALYSES OF FLUID FLOW AND HEAT TRANSFER IN PATTERNED ROLL-BONDED ALUMINIUM PLATE RADIATORS Third International Conference on CFD in the Minerals and Process Industries CSIRO, Melbourne, Australia 10-12 December 2003 CFD ANALYSES OF FLUID FLOW AND HEAT TRANSFER IN PATTERNED ROLL-BONDED ALUMINIUM

More information

Science Insights: An International Journal

Science Insights: An International Journal Available online at http://www.urpjournals.com Science Insights: An International Journal Universal Research Publications. All rights reserved Original Article CENTRIFUGAL COMPRESSOR FLUID FLOW ANALYSIS

More information

Practice Problems on Boundary Layers. Answer(s): D = 107 N D = 152 N. C. Wassgren, Purdue University Page 1 of 17 Last Updated: 2010 Nov 22

Practice Problems on Boundary Layers. Answer(s): D = 107 N D = 152 N. C. Wassgren, Purdue University Page 1 of 17 Last Updated: 2010 Nov 22 BL_01 A thin flat plate 55 by 110 cm is immersed in a 6 m/s stream of SAE 10 oil at 20 C. Compute the total skin friction drag if the stream is parallel to (a) the long side and (b) the short side. D =

More information

O.F.Wind Wind Site Assessment Simulation in complex terrain based on OpenFOAM. Darmstadt, 27.06.2012

O.F.Wind Wind Site Assessment Simulation in complex terrain based on OpenFOAM. Darmstadt, 27.06.2012 O.F.Wind Wind Site Assessment Simulation in complex terrain based on OpenFOAM Darmstadt, 27.06.2012 Michael Ehlen IB Fischer CFD+engineering GmbH Lipowskystr. 12 81373 München Tel. 089/74118743 Fax 089/74118749

More information

CFD Study on the Diffuser of a Formula 3 Racecar

CFD Study on the Diffuser of a Formula 3 Racecar CFD Study on the Diffuser of a Formula 3 Racecar Kevin M. Peddie, Luis F. Gonzalez School of Aerospace, Mechanical and Mechatronic Engineering University of Sydney ABSTRACT The primary goal of the paper

More information

Part IV. Conclusions

Part IV. Conclusions Part IV Conclusions 189 Chapter 9 Conclusions and Future Work CFD studies of premixed laminar and turbulent combustion dynamics have been conducted. These studies were aimed at explaining physical phenomena

More information

CFD Based Air Flow and Contamination Modeling of Subway Stations

CFD Based Air Flow and Contamination Modeling of Subway Stations CFD Based Air Flow and Contamination Modeling of Subway Stations Greg Byrne Center for Nonlinear Science, Georgia Institute of Technology Fernando Camelli Center for Computational Fluid Dynamics, George

More information

EFFECT OF OBSTRUCTION NEAR FAN INLET ON FAN HEAT SINK PERFORMANCE

EFFECT OF OBSTRUCTION NEAR FAN INLET ON FAN HEAT SINK PERFORMANCE EFFECT OF OBSTRUCTION NEAR FAN INLET ON FAN HEAT SINK PERFORMANCE Vivek Khaire, Dr. Avijit Goswami Applied Thermal Technologies India 3rd Floor,C-Wing,Kapil Towers, Dr. Ambedkar Road, Pune- 411 1 Maharashtra,

More information

AUTOMOTIVE COMPUTATIONAL FLUID DYNAMICS SIMULATION OF A CAR USING ANSYS

AUTOMOTIVE COMPUTATIONAL FLUID DYNAMICS SIMULATION OF A CAR USING ANSYS International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 2, March-April 2016, pp. 91 104, Article ID: IJMET_07_02_013 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=7&itype=2

More information

Ravi Kumar Singh*, K. B. Sahu**, Thakur Debasis Mishra***

Ravi Kumar Singh*, K. B. Sahu**, Thakur Debasis Mishra*** Ravi Kumar Singh, K. B. Sahu, Thakur Debasis Mishra / International Journal of Engineering Research and Applications (IJERA) ISSN: 48-96 www.ijera.com Vol. 3, Issue 3, May-Jun 3, pp.766-77 Analysis of

More information

CFD Lab Department of Engineering The University of Liverpool

CFD Lab Department of Engineering The University of Liverpool Development of a CFD Method for Aerodynamic Analysis of Large Diameter Horizontal Axis wind turbines S. Gomez-Iradi, G.N. Barakos and X. Munduate 2007 joint meeting of IEA Annex 11 and Annex 20 Risø National

More information

ME6130 An introduction to CFD 1-1

ME6130 An introduction to CFD 1-1 ME6130 An introduction to CFD 1-1 What is CFD? Computational fluid dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions, and related phenomena by solving numerically

More information

Adaptation of General Purpose CFD Code for Fusion MHD Applications*

Adaptation of General Purpose CFD Code for Fusion MHD Applications* Adaptation of General Purpose CFD Code for Fusion MHD Applications* Andrei Khodak Princeton Plasma Physics Laboratory P.O. Box 451 Princeton, NJ, 08540 USA akhodak@pppl.gov Abstract Analysis of many fusion

More information

MAXIMISING THE HEAT TRANSFER THROUGH FINS USING CFD AS A TOOL

MAXIMISING THE HEAT TRANSFER THROUGH FINS USING CFD AS A TOOL MAXIMISING THE HEAT TRANSFER THROUGH FINS USING CFD AS A TOOL Sanjay Kumar Sharma 1 and Vikas Sharma 2 1,2 Assistant Professor, Department of Mechanical Engineering, Gyan Vihar University, Jaipur, Rajasthan,

More information

Computational Modeling of Wind Turbines in OpenFOAM

Computational Modeling of Wind Turbines in OpenFOAM Computational Modeling of Wind Turbines in OpenFOAM Hamid Rahimi hamid.rahimi@uni-oldenburg.de ForWind - Center for Wind Energy Research Institute of Physics, University of Oldenburg, Germany Outline Computational

More information

COMPUTATIONAL ANALYSIS OF CENTRIFUGAL COMPRESSOR WITH GROOVES ON CASING

COMPUTATIONAL ANALYSIS OF CENTRIFUGAL COMPRESSOR WITH GROOVES ON CASING INTERNATIONAL JOURNAL OF MECHANICAL ENGINEERING AND TECHNOLOGY (IJMET) International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 6340(Print), ISSN ISSN 0976 6340 (Print) ISSN 0976

More information

Modelling and Computation of Compressible Liquid Flows with Phase Transition

Modelling and Computation of Compressible Liquid Flows with Phase Transition JASS 2009 - Joint Advanced Student School, Saint Petersburg, 29. 03. - 07. 04. 2009 Modelling and Simulation in Multidisciplinary Engineering Modelling and Computation of Compressible Liquid Flows with

More information

Lab 1a Wind Tunnel Testing Principles & Lift and Drag Coefficients on an Airfoil

Lab 1a Wind Tunnel Testing Principles & Lift and Drag Coefficients on an Airfoil Lab 1a Wind Tunnel Testing Principles & Lift and Drag Coefficients on an Airfoil OBJECTIVES - Calibrate the RPM/wind speed relation of the wind tunnel. - Measure the drag and lift coefficients of an airfoil

More information

Experimental Wind Turbine Aerodynamics Research @LANL

Experimental Wind Turbine Aerodynamics Research @LANL Experimental Wind Turbine Aerodynamics Research @LANL B. J. Balakumar, Los Alamos National Laboratory Acknowledgment: SuhasPol(Post-doc), John Hoffman, Mario Servin, Eduardo Granados (Summer students),

More information

A LAMINAR FLOW ELEMENT WITH A LINEAR PRESSURE DROP VERSUS VOLUMETRIC FLOW. 1998 ASME Fluids Engineering Division Summer Meeting

A LAMINAR FLOW ELEMENT WITH A LINEAR PRESSURE DROP VERSUS VOLUMETRIC FLOW. 1998 ASME Fluids Engineering Division Summer Meeting TELEDYNE HASTINGS TECHNICAL PAPERS INSTRUMENTS A LAMINAR FLOW ELEMENT WITH A LINEAR PRESSURE DROP VERSUS VOLUMETRIC FLOW Proceedings of FEDSM 98: June -5, 998, Washington, DC FEDSM98 49 ABSTRACT The pressure

More information

IPACK2005-73273 DISTRIBUTED LEAKAGE FLOW IN RAISED-FLOOR DATA CENTERS

IPACK2005-73273 DISTRIBUTED LEAKAGE FLOW IN RAISED-FLOOR DATA CENTERS Proceedings of IPACK5 ASME InterPACK '5 July 17-, San Francisco, California, USA IPACK5-7373 DISTRIBUTED LEAKAGE FLOW IN RAISED-FLOOR DATA CENTERS Amir Radmehr Innovative Research, Inc. Plymouth, MN, USA

More information

RANS SIMULATION OF RAF6 AIRFOIL

RANS SIMULATION OF RAF6 AIRFOIL RANS SIMULATION OF RAF6 AIRFOIL László NAGY Ph.D. Student, Budapest University of Technology and Economics János VAD Associate Professor, Budapest University of Technology and Economics Máté Márton LOHÁSZ

More information

Fundamentals of Fluid Mechanics

Fundamentals of Fluid Mechanics Sixth Edition. Fundamentals of Fluid Mechanics International Student Version BRUCE R. MUNSON DONALD F. YOUNG Department of Aerospace Engineering and Engineering Mechanics THEODORE H. OKIISHI Department

More information

RAISED-FLOOR DATA CENTER: PERFORATED TILE FLOW RATES FOR VARIOUS TILE LAYOUTS

RAISED-FLOOR DATA CENTER: PERFORATED TILE FLOW RATES FOR VARIOUS TILE LAYOUTS Paper Presented at ITHERM 2004 Ninth Intersociety Conference on Thermal and Thermomechanical Phenomena in Electronic Systems June 1-4, Las Vegas, NV RAISED-FLOOR DATA CENTER: PERFORATED TILE FLOW RATES

More information

Effect of Aspect Ratio on Laminar Natural Convection in Partially Heated Enclosure

Effect of Aspect Ratio on Laminar Natural Convection in Partially Heated Enclosure Universal Journal of Mechanical Engineering (1): 8-33, 014 DOI: 10.13189/ujme.014.00104 http://www.hrpub.org Effect of Aspect Ratio on Laminar Natural Convection in Partially Heated Enclosure Alireza Falahat

More information

NUMERICAL ANALYSIS OF WELLS TURBINE FOR WAVE POWER CONVERSION

NUMERICAL ANALYSIS OF WELLS TURBINE FOR WAVE POWER CONVERSION Engineering Review Vol. 32, Issue 3, 141-146, 2012. 141 NUMERICAL ANALYSIS OF WELLS TURBINE FOR WAVE POWER CONVERSION Z. 1* L. 1 V. 2 M. 1 1 Department of Fluid Mechanics and Computational Engineering,

More information

Application of Wray-Agarwal Model to Turbulent Flow in a 2D Lid-Driven Cavity and a 3D Lid- Driven Box

Application of Wray-Agarwal Model to Turbulent Flow in a 2D Lid-Driven Cavity and a 3D Lid- Driven Box Washington University in St. Louis Washington University Open Scholarship Engineering and Applied Science Theses & Dissertations Engineering and Applied Science Summer 8-14-2015 Application of Wray-Agarwal

More information

CFD ANALAYSIS OF FLOW THROUGH A CONICAL EXHAUST DIFFUSER

CFD ANALAYSIS OF FLOW THROUGH A CONICAL EXHAUST DIFFUSER CFD ANALAYSIS OF FLOW THROUGH A CONICAL EXHAUST DIFFUSER R.Prakash 1, D.Christopher 2, K.Kumarrathinam 3 1 Assistant Professor, Department of Mechanical Engineering, SSN College of Engineering, Tamil Nadu,

More information

THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA

THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA Adam Kosík Evektor s.r.o., Czech Republic KEYWORDS CFD simulation, mesh generation, OpenFOAM, ANSA ABSTRACT In this paper we describe

More information

High Speed Aerodynamics Prof. K. P. Sinhamahapatra Department of Aerospace Engineering Indian Institute of Technology, Kharagpur

High Speed Aerodynamics Prof. K. P. Sinhamahapatra Department of Aerospace Engineering Indian Institute of Technology, Kharagpur High Speed Aerodynamics Prof. K. P. Sinhamahapatra Department of Aerospace Engineering Indian Institute of Technology, Kharagpur Module No. # 01 Lecture No. # 06 One-dimensional Gas Dynamics (Contd.) We

More information

Lecture 11 Boundary Layers and Separation. Applied Computational Fluid Dynamics

Lecture 11 Boundary Layers and Separation. Applied Computational Fluid Dynamics Lecture 11 Boundary Layers and Separation Applied Computational Fluid Dynamics Instructor: André Bakker http://www.bakker.org André Bakker (2002-2006) Fluent Inc. (2002) 1 Overview Drag. The boundary-layer

More information

du u U 0 U dy y b 0 b

du u U 0 U dy y b 0 b BASIC CONCEPTS/DEFINITIONS OF FLUID MECHANICS (by Marios M. Fyrillas) 1. Density (πυκνότητα) Symbol: 3 Units of measure: kg / m Equation: m ( m mass, V volume) V. Pressure (πίεση) Alternative definition:

More information

SBi 2013:12. Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems

SBi 2013:12. Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems SBi 2013:12 Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems

More information

FLOW CONDITIONER DESIGN FOR IMPROVING OPEN CHANNEL FLOW MEASUREMENT ACCURACY FROM A SONTEK ARGONAUT-SW

FLOW CONDITIONER DESIGN FOR IMPROVING OPEN CHANNEL FLOW MEASUREMENT ACCURACY FROM A SONTEK ARGONAUT-SW FLOW CONDITIONER DESIGN FOR IMPROVING OPEN CHANNEL FLOW MEASUREMENT ACCURACY FROM A SONTEK ARGONAUT-SW Daniel J. Howes, P.E. 1 Charles M. Burt, Ph.D., P.E. 2 Brett F. Sanders, Ph.D. 3 ABSTRACT Acoustic

More information

Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology

Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology Dimitrios Sofialidis Technical Manager, SimTec Ltd. Mechanical Engineer, PhD PRACE Autumn School 2013 - Industry

More information

Comparison of Various Supersonic Turbine Tip Designs to Minimize Aerodynamic Loss and Tip Heating

Comparison of Various Supersonic Turbine Tip Designs to Minimize Aerodynamic Loss and Tip Heating NASA/TM 2012-217607 GT2011 46390 Comparison of Various Supersonic Turbine Tip Designs to Minimize Aerodynamic Loss and Tip Heating Vikram Shyam Glenn Research Center, Cleveland, Ohio Ali Ameri The Ohio

More information

Experimental Evaluation of the Discharge Coefficient of a Centre-Pivot Roof Window

Experimental Evaluation of the Discharge Coefficient of a Centre-Pivot Roof Window Experimental Evaluation of the Discharge Coefficient of a Centre-Pivot Roof Window Ahsan Iqbal #1, Alireza Afshari #2, Per Heiselberg *3, Anders Høj **4 # Energy and Environment, Danish Building Research

More information

Basic Equations, Boundary Conditions and Dimensionless Parameters

Basic Equations, Boundary Conditions and Dimensionless Parameters Chapter 2 Basic Equations, Boundary Conditions and Dimensionless Parameters In the foregoing chapter, many basic concepts related to the present investigation and the associated literature survey were

More information

HEAT TRANSFER AUGMENTATION IN A PLATE-FIN HEAT EXCHANGER: A REVIEW

HEAT TRANSFER AUGMENTATION IN A PLATE-FIN HEAT EXCHANGER: A REVIEW International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 1, Jan-Feb 2016, pp. 37-41, Article ID: IJMET_07_01_005 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=7&itype=1

More information

GT2011 46090 ANALYSIS OF A MICROGASTURBINE FED BY NATURAL GAS AND SYNTHESIS GAS: MGT TEST BENCH AND COMBUSTOR CFD ANALYSIS

GT2011 46090 ANALYSIS OF A MICROGASTURBINE FED BY NATURAL GAS AND SYNTHESIS GAS: MGT TEST BENCH AND COMBUSTOR CFD ANALYSIS ASME Turbo Expo 2011 June 6 10, 2011 Vancouver, Canada GT 2011 46090 ANALYSIS OF A MICROGASTURBINE FED BY NATURAL GAS AND SYNTHESIS GAS: MGT TEST BENCH AND COMBUSTOR CFD ANALYSIS M. Cadorin 1,M. Pinelli

More information

CFD Analysis on Airfoil at High Angles of Attack

CFD Analysis on Airfoil at High Angles of Attack CFD Analysis on Airfoil at High Angles of Attack Dr.P.PrabhakaraRao¹ & Sri Sampath.V² Department of Mechanical Engineering,Kakatiya Institute of Technology& Science Warangal-506015 1 chantifft@rediffmail.com,

More information

FLUID FLOW Introduction General Description

FLUID FLOW Introduction General Description FLUID FLOW Introduction Fluid flow is an important part of many processes, including transporting materials from one point to another, mixing of materials, and chemical reactions. In this experiment, you

More information

Numerical Investigation of Heat Transfer Characteristics in A Square Duct with Internal RIBS

Numerical Investigation of Heat Transfer Characteristics in A Square Duct with Internal RIBS merical Investigation of Heat Transfer Characteristics in A Square Duct with Internal RIBS Abhilash Kumar 1, R. SaravanaSathiyaPrabhahar 2 Mepco Schlenk Engineering College, Sivakasi, Tamilnadu India 1,

More information

Experimental Study of Free Convection Heat Transfer From Array Of Vertical Tubes At Different Inclinations

Experimental Study of Free Convection Heat Transfer From Array Of Vertical Tubes At Different Inclinations Experimental Study of Free Convection Heat Transfer From Array Of Vertical Tubes At Different Inclinations A.Satyanarayana.Reddy 1, Suresh Akella 2, AMK. Prasad 3 1 Associate professor, Mechanical Engineering

More information

Problem Statement In order to satisfy production and storage requirements, small and medium-scale industrial

Problem Statement In order to satisfy production and storage requirements, small and medium-scale industrial Problem Statement In order to satisfy production and storage requirements, small and medium-scale industrial facilities commonly occupy spaces with ceilings ranging between twenty and thirty feet in height.

More information