CHAPTER 1 INTRODUCTION

Size: px
Start display at page:

Download "CHAPTER 1 INTRODUCTION"

Transcription

1 CHAPTER 1 INTRODUCTION Wind tunnel is a large tube with air moving inside which is used to copy the actions of an object in flight. In wind tunnel air moves around an object, so the object seems like really flying. Although the form of a wind tunnel can vary, all wind tunnels have a high pressure system, heater, settling chamber and a test section. Air is compressed and stored in the high pressure system. It is released through a pressure regulating valve to create the desired pressure in the settling chamber. In high speed wind tunnels, heater is used to heat the air while passing through the heater bed to avoid liquefaction when it is expanded through the nozzle to get high Mach numbers. Scaled models of aircraft or space craft are placed in the test section for testing as shown in Figure 1.1. Some wind tunnels are big enough to hold full- scale versions of vehicles. Figure 1.1: Wind tunnel with the model of a plane. (Courtesy : Wikipedia) 1

2 Air is blown or sucked through a duct equipped with a viewing port and instrumentation where models or geometrical shapes are mounted for study. The movement of air through the tunnel is done by using a series of fans, which are usually powered by stationary turbo rather than electric motors. Vertical and horizontal air vanes make the turbulent air flow smooth, before reaching the test section. The cross section of the tunnel is circular to provide a smoother air flow. The smooth inner surface reduces the surface drag. The circular walls of the tunnel are usually embedded with light, which shines through the windows. Pressure taps are included in the model for measuring pressure. Lift, drag, yaw, roll, lateral forces and pitching moments over a range of angle of attack can be measured by a force balance mounted on the model. The movement of air around the model is difficult to observe directly, since air is transparent. Different flow visualization methods have been developed for testing in a wind tunnel. Tufts attached to the model during testing can be used to gauge air flow. Another method is by using evaporating suspensions, where the liquid evaporates leaving behind the clay in the pattern characteristic of the air flow. Applying oil to the surface of the model can show the transition from laminar to turbulent flow as well as flow separation. Smoke or bubbles of liquid can be introduced into the airflow upstream of the test model, so that their path around the model can be photographed. 1.1 TYPES OF WIND TUNNEL Wind tunnels can be classified based on air flow speed in test section and based on shape. Flow speed in wind tunnel is generally referred in terms of Mach number. Mach number is a dimensionless quantity representing the ratio of speed of an object moving through a medium and the local speed of 2

3 sound. Based on flow speed, wind tunnels are classified as Subsonic, Transonic, Supersonic and Hypersonic. In Subsonic or low speed wind tunnels flow speed in terms of Mach number comes out to be around 0.4. These types of wind tunnels are most cost effective due to the simplicity of the design and low wind speed. Generally low speed wind tunnels are used in schools and universities because of low budget. Maximum velocity in test section of transonic wind tunnels can reach up to speed of sound i.e. 340m/s or Mach number of 1. They are very common in aircraft industry as most aircrafts operate around this speed. Velocity of air in test section of Supersonic wind tunnels wind tunnels can be up to Mach 5. This is accomplished using convergent or divergent nozzles and the power requirements for such wind tunnels are very high. Hypersonic wind tunnels can have wind velocity in test section between Mach 5 and Mach 15. This is also achieved using convergent - divergent nozzles. They are used to test ultra fast air craft and space vehicles. The technological problems in designing and constructing a hyper-velocity wind tunnel are supply of high temperatures and pressures for times long enough to perform a measurement, reproduction of equilibrium conditions, structural damage produced by overheating, fast instrumentation and power requirements to run the tunnel. Based on shape, wind tunnels are classified as Open circuit wind tunnel and Closed circuit wind tunnel. Open circuit wind tunnel is open at both ends. The chances of dirt particles entering with air are more and so more honeycombs (mesh to clean incoming air) are required for cleaning the air. Open type wind tunnels can further be divided into two categories: Suckdown tunnel and Blower tunnel. In Suckdown tunnel, the inlet open to atmosphere and the axial fan or centrifugal blower is connected after the test 3

4 section. These types of wind tunnels are not preferred because incoming air enters with significant swirl. In blower tunnel a blower is installed at the inlet of wind tunnel which throws the air into wind tunnel. For supersonic and hypersonic type wind tunnel, the desired speed cannot be attained with the help of a blower. Hence a tank with high air pressure is maintained and the flow is obtained by releasing the air from this high pressure system. Outlet of closed circuit wind tunnel is connected to inlet and so the same air circulates in the system in a regulated way. The chances of dirt entering the system are very low. Closed wind tunnels have more uniform flow compared to open type. Closed tunnel is usually a choice for large wind tunnels as these are more costly than open type wind tunnels. 1.2 RELEVANCE OF WIND TUNNEL One of the main aims of using a wind tunnel is to learn more about air planes and how things move through air and thereby improving air transportation. It helps scientists to make aircraft better and safer. New materials or shapes for airplane parts can be tested before flying in a wind tunnel to make it sure it will fly as it should. Wind tunnels are also used to test spacecraft and rockets, which are made to operate in space, where there is no atmosphere. They have to travel through the atmosphere before entering the space. Vehicles that take humans into space also must come back through the atmosphere to Earth. The wind tunnel is a major money saver. It allows us to make a reusable prototype and test it in the tunnel at low cost. Wind tunnels are important in making the new Ares rockets and Orion space shuttle which are vehicles that will take astronauts into space. Ares 4

5 rockets were planned for using to launch Orion, which is the spacecraft intended for NASA human spaceflight missions. NASA engineers tested ideas for the design of Ares in wind tunnels, to see how well Ares would fly. Engineers tested Orion models to know what would happen to different designs when the spacecraft came back through the atmosphere. Wind tunnels can even help engineers design spacecraft to work on other worlds. Mars has a thin atmosphere and it is important to know what the Martian atmosphere will do to vehicles that are landing there. Parachutes and spacecraft designs are tested in wind tunnels set up to be like the Martian atmosphere. In modern automotive design, the aerodynamic design plays an important role, which determines vehicle s fuel consumption, stability, engine cooling, interior cabin noise and windshield-wiper performance. Wind tunnel simulations allow engineers to study these aerodynamic loads during a newly designed vehicle s development process. Wind tunnels are used in Wind Engineering, to measure the velocity around and pressure or forces upon structures. Specialized atmospheric boundary layer wind tunnels are used to analyze the wind speed and turbulence profile acting on very tall buildings, buildings with complicated or unusual shapes like a hyperbolic or parabolic shape, cable suspension bridges or cable stayed bridges. Aerodynamics are important in almost every sports ie, from ball games like golf, baseball, soccer, football and tennis to athletics, alpine skiing, crosscountry skiing, ski jumping, cycling, motor sport and many others, where the performance results in the optimal motion of the athlete (multi-jointed mechanical system) and/or is equipment (solid system) in the air. Athletes can 5

6 assess the aerodynamic efficiency of the motor task performed by him with accuracy and in almost real time in a wind tunnel, which help them to focus on specific aspects of his technical behavior to improve his performance. Thus wind tunnels are an excellent example of a technological innovation that supports aircraft and space craft design. They are not simply a tube or box with a fan blowing air but are carefully designed and constructed (and often very large) laboratory instruments. Without constant research in wind tunnel technology, aeronautical research would have ground to a standstill decades ago. 1.3 NEED FOR PROPER CONTROLLER IN A WIND TUNNEL The wind tunnel in this thesis is Hypersonic Blowdown type, which can hit hypersonic speeds of up to 12 Mach numbers. Here there is a high pressure system, from which air is released using a pressure regulating valve, to get the desired flow in the test section. To get the hypersonic speed in the test section, the mass flow rate of the air in the test section has to be maintained constant. Mass flow rate is the mass of a substance which passes through a given surface per unit of time. To attain constant mass flow rate, the pressure in the settling chamber, whose output is given to the test section has to be maintained constant. This can be achieved by controlling the opening of pressure regulating valve. So it is needed to design a controller, which will regulate the operation of the control valve, to get a constant pressure in the settling chamber. The controller has to act within few seconds, since the system exists for very short duration. To obtain accurate, stable air flow and to provide proper operation of the HWT system an efficient controller is required. As the system behavior is changing with time, the controller has to adapt itself to the changes in 6

7 operating environment. PI or PID controllers (conventional controllers) are suitable for linear systems. For nonlinear systems, we can use conventional controllers only if the operating range is limited. It will give satisfactory response only at the point of linearization. Its performance degrades as the operating point moves away from the point of linearization. Artificial Neural Network based adaptive controllers are not suitable as they take more time to learn the system behavior through weight updation. Scheduled adaptive controllers are not practicable in this case since scheduling the control by forming a lookup table is tedious. As the system behavior is changing from time to time, a perfect lookup table can only be constructed with infinite entries. Self tuning regulators (STR) are based on a parameter estimator and its performance heavily depends on the robustness of the estimation algorithm used. Model reference adaptive controllers can be a reasonable solution in such a situation. But its performance also depends on the reference model used. If we incorporate fast adaptation techniques with conventional controllers it can be a reasonable solution. 1.4 OBJECTIVES The main objectives of this thesis work are To simulate the operation of a Hypersonic Wind Tunnel (HWT) and to study its behavior and non linearity. To design and implement different controllers for the process which satisfies the following requirements. o To bring the pressure in the settling chamber of a HWT to the desired value in less than 10 sec. o To increase the test duration as longer as possible. 7

8 o To make the overshoot of the system less than 20%. o To minimize the error during test time. o To reduce the effect of external disturbance as low as possible in terms of error and settling time. And finally, to suggest a controller which meets all/ most of the above requirements for the HWT. 1.5 METHODOLOGY Several procedural steps are followed to achieve the objective of this research work. Initially the mathematical model of the HWT is simulated using the simulink tool in MATLab. The model developed is validated and nonlinearity of the system is analyzed. Further, different non linear controllers for the process are designed and simulated, for different set points. Performances of all these controllers were evaluated through the servo and regulator operation. A detailed analysis of the performance parameters were done for all these different controllers and finally, the optimum controller for the process is suggested. Figure1.2. The framework for solving the problem defined above is shown in 8

9 Figure 1.2 Block diagram of proposed work 1.6 ORGANIZATION OF THE THESIS The rest of the thesis is organized as follows. A comprehensive review of literature on the wind tunnel and various controllers are presented in Chapter 2. The literature survey on historical background of wind tunnel is also included in this chapter. 9

10 Chapter 3 provides the detailed information on the system model of hypersonic wind tunnel along with the validity of the model and its analysis of nonlinearity. In this chapter the need for controller and its analysis are also discussed. Chapter 4 describes the PI controller design methodology for Hypersonic Wind Tunnel. The performance evaluation of the PI controller is done and is presented along with the simulation results. Chapter 5 discusses the application of Fuzzy technique for assisting the PI controller. Performance analysis and evaluation of the controller is also made here. Chapter 6 covers the Backstepping controller design techniques for regulating pressure in a HWT. The techniques discussed in this chapter are the tracking and stabilizing designs of Backstepping controller, and also the combination of Backstepping with Fuzzy controller. The servo and regulator operation of the controller is simulated and the results are tabulated for performance evaluation. Chapter 7 contains the design and evaluation of the single stage and two stage Cascade controllers. The chapter summarizes the performance of two stage cascade controller. Chapter 8 presents performance analysis of the Model Reference Fuzzy Adaptive PI Controller along with Model Reference Fuzzy Cascade Controller. 10

11 The performance evaluations of these controllers were done by applying servo and regulator operations for different set points. The simulation results of each controller are analyzed in the respective chapters. The chapter 9 gives the comparative analysis of the controller s performance, summary of work done and the contribution of the work. 11

Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle

Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle RESEARCH ARTICLE OPEN ACCESS Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle Shyamshankar.M.B*, Sankar.V** *(Department of Aeronautical

More information

Applied Fluid Mechanics

Applied Fluid Mechanics Applied Fluid Mechanics 1. The Nature of Fluid and the Study of Fluid Mechanics 2. Viscosity of Fluid 3. Pressure Measurement 4. Forces Due to Static Fluid 5. Buoyancy and Stability 6. Flow of Fluid and

More information

PI control for regulating pressure inside a hypersonic wind tunnel

PI control for regulating pressure inside a hypersonic wind tunnel PI control for regulating pressure inside a hypersonic wind tunnel Sameer U. Ranade Dept of Electrical engineering, Walchand College of Engineering, Vishrambag, Sangli.416415. State- Maharshtra Email:

More information

Lab # 03: Visualization of Shock Waves by using Schlieren Technique

Lab # 03: Visualization of Shock Waves by using Schlieren Technique AerE545 Lab # 03: Visualization of Shock Waves by using Schlieren Technique Objectives: 1. To get hands-on experiences about Schlieren technique for flow visualization. 2. To learn how to do the optics

More information

ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT

ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT P.Sethunathan 1, M.Niventhran 2, V.Siva 2, R.Sadhan Kumar 2 1 Asst.Professor, Department of Aeronautical Engineering,

More information

Reduction of Skin Friction Drag in Wings by Employing Riblets

Reduction of Skin Friction Drag in Wings by Employing Riblets Reduction of Skin Friction Drag in Wings by Employing Riblets Kousik Kumaar. R 1 Assistant Professor Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Coimbatore, India

More information

C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory

C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory ROAD MAP... AE301 Aerodynamics I UNIT C: 2-D Airfoils C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory AE301 Aerodynamics I : List of Subjects

More information

CFD Study of Solid Wind Tunnel Wall Effects on Wing Characteristics

CFD Study of Solid Wind Tunnel Wall Effects on Wing Characteristics Indian Journal of Science and Technology, Vol 9(45), DOI :10.17485/ijst/2016/v9i45/104585, December 2016 ISSN (Print) : 0974-6846 ISSN (Online) : 0974-5645 CFD Study of Solid Wind Tunnel Wall Effects on

More information

5th Symposium on Integrating CFD and Experiments in Aerodynamics (Integration 2012) th Symposium on Integrating CFD and Experiments in Aerodynam

5th Symposium on Integrating CFD and Experiments in Aerodynamics (Integration 2012) th Symposium on Integrating CFD and Experiments in Aerodynam 5th Symposium on Integrating CFD and Experiments in Aerodynamics (Integration 202) 36 Multi-objective Optimization of Airfoil of Mars Exploration Aircraft using Evolutionary Algorithm Gaku Sasaki Tomoaki

More information

AF100. Subsonic Wind Tunnel AERODYNAMICS. Open-circuit subsonic wind tunnel for a wide range of investigations into aerodynamics

AF100. Subsonic Wind Tunnel AERODYNAMICS. Open-circuit subsonic wind tunnel for a wide range of investigations into aerodynamics Open-circuit subsonic wind tunnel for a wide range of investigations into aerodynamics Page 1 of 4 Works with Computer, chair and work table shown for photographic purposes only (not included) Screenshot

More information

A. M. Dalavi, Mahesh Jadhav, Yasin Shaikh, Avinash Patil (Department of Mechanical Engineering, Symbiosis Institute of Technology, India)

A. M. Dalavi, Mahesh Jadhav, Yasin Shaikh, Avinash Patil (Department of Mechanical Engineering, Symbiosis Institute of Technology, India) IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) ISSN(e) : 2278-1684, ISSN(p) : 2320 334X, PP : 45-49 www.iosrjournals.org Modeling, Optimization & Manufacturing of Vortex Tube and Application

More information

Flutter Testing. Wind Tunnel Testing (excerpts from Reference 1)

Flutter Testing. Wind Tunnel Testing (excerpts from Reference 1) Flutter Testing In the early years of aviation, no formal flutter testing of aircraft was performed. Flutter was usually discovered by accident during flight of the aircraft. The pilot flew the aircraft

More information

Effect of Co-Flow Jet over an Airfoil: Numerical Approach

Effect of Co-Flow Jet over an Airfoil: Numerical Approach Contemporary Engineering Sciences, Vol. 7, 2014, no. 17, 845-851 HIKARI Ltd, www.m-hikari.com http://dx.doi.org/10.12988/ces.2014.4655 Effect of Co-Flow Jet over an Airfoil: Numerical Approach Md. Riajun

More information

Investigation of Suction Process of Scroll Compressors

Investigation of Suction Process of Scroll Compressors Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 2006 Investigation of Suction Process of Scroll Compressors Michael M. Cui Trane Jack Sauls

More information

Design of a Solid Wall Transonic Wind Tunnel

Design of a Solid Wall Transonic Wind Tunnel Design of a Solid Wall Transonic Wind Tunnel David Wall * Auburn University, Auburn, Alabama, 36849 A solid wall transonic wind tunnel was designed with optical access from three sides to allow for flow

More information

Flight Corridor. The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor.

Flight Corridor. The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor. Flight Corridor The speed-altitude band where flight sustained by aerodynamic forces is technically possible is called the flight corridor. The subsonic Boeing 747 and supersonic Concorde have flight corridors

More information

Investigation on 3-D Wing of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent

Investigation on 3-D Wing of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent Investigation on 3-D of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent Rohit Jain 1, Mr. Sandeep Jain 2, Mr. Lokesh Bajpai 3 1PG Student, 2 Associate Professor, 3 Professor & Head 1 2 3

More information

Lift for a Finite Wing. all real wings are finite in span (airfoils are considered as infinite in the span)

Lift for a Finite Wing. all real wings are finite in span (airfoils are considered as infinite in the span) Lift for a Finite Wing all real wings are finite in span (airfoils are considered as infinite in the span) The lift coefficient differs from that of an airfoil because there are strong vortices produced

More information

The Quarter Pounder A Vehicle to Launch Quarter Pound Payloads to Low Earth Orbit

The Quarter Pounder A Vehicle to Launch Quarter Pound Payloads to Low Earth Orbit The Quarter Pounder A Vehicle to Launch Quarter Pound Payloads to Low Earth Orbit Ed LeBouthillier 1 Contents Introduction... 3 Requirements... 4 Orbital Altitudes... 4 Orbital Velocities... 4 Summary...4

More information

Subsonic Wind Tunnel 300 mm

Subsonic Wind Tunnel 300 mm aerodynamics AF1300 An open circuit suction subsonic wind tunnel with a working section of 300 mm by 300 mm and 600 mm long Screenshot of the optional VDAS software Saves time and money compared to full-scale

More information

Welcome to Aerospace Engineering

Welcome to Aerospace Engineering Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 4 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route

More information

ZIN Technologies PHi Engineering Support. PHi-RPT CFD Analysis of Large Bubble Mixing. June 26, 2006

ZIN Technologies PHi Engineering Support. PHi-RPT CFD Analysis of Large Bubble Mixing. June 26, 2006 ZIN Technologies PHi Engineering Support PHi-RPT-0002 CFD Analysis of Large Bubble Mixing Proprietary ZIN Technologies, Inc. For nearly five decades, ZIN Technologies has provided integrated products and

More information

Wind Tunnel Instrumentation System

Wind Tunnel Instrumentation System Wind Tunnel Instrumentation System Karthigeyan S 1, Jai bhavani K S 2, Jenifer Z 3 P.G Student, Dept. of, Valliammai Engineering College, Chennai, India 1 Assistant Professor, Dept. of, Valliammai Engineering

More information

PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL

PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL S R Bhoi and G K Suryanarayana National Trisonic Aerodynamic Facilities, National Aerospace Laboratories,

More information

A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier

A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier Jeon-gi Lee*, Choul-jun Choi*, Nam-su Kwak*, Su-sang Park*

More information

DESIGN AND CHARACTERISTICS OF A LARGE BOUNDARY- LAYER WIND TUNNEL WITH TWO TEST SECTIONS

DESIGN AND CHARACTERISTICS OF A LARGE BOUNDARY- LAYER WIND TUNNEL WITH TWO TEST SECTIONS The Seventh Asia-Pacific Conference on Wind Engineering, November 8-12, 2009, Taipei, Taiwan DESIGN AND CHARACTERISTICS OF A LARGE BOUNDARY- LAYER WIND TUNNEL WITH TWO TEST SECTIONS Kai Chen 1, Xin-Yang

More information

Low Speed Wind Tunnel Wing Performance

Low Speed Wind Tunnel Wing Performance Low Speed Wind Tunnel Wing Performance ARO 101L Introduction to Aeronautics Section 01 Group 13 20 November 2015 Aerospace Engineering Department California Polytechnic University, Pomona Team Leader:

More information

Flying High. HHJS Science Week Background Information. Forces and Flight

Flying High. HHJS Science Week Background Information. Forces and Flight Flying High HHJS Science Week 2013 Background Information Forces and Flight Flight Background Information Flying is defined as controlled movement through the air. Many things can become airborne but this

More information

The subsonic compressibility effect is added by replacing. with

The subsonic compressibility effect is added by replacing. with Swept Wings The main function of a swept wing is to reduce wave drag at transonic and supersonic speeds. Consider a straight wing and a swept wing in a flow with a free-stream velocity V. Assume that the

More information

Four forces on an airplane

Four forces on an airplane Four forces on an airplane By NASA.gov on 10.12.16 Word Count 824 Level MAX TOP: An airplane pictured on June 30, 2016. Courtesy of Pexels. BOTTOM: Four forces on an airplane. Courtesy of NASA. A force

More information

Detailed study 3.4 Topic Test Investigations: Flight

Detailed study 3.4 Topic Test Investigations: Flight Name: Billanook College Detailed study 3.4 Topic Test Investigations: Flight Ivanhoe Girls Grammar School Questions 1 and 2 relate to the information shown in the diagram in Figure 1. z Question 1 y Figure

More information

Inlet Influence on the Pressure and Temperature Distortion Entering the Compressor of an Air Vehicle

Inlet Influence on the Pressure and Temperature Distortion Entering the Compressor of an Air Vehicle Distortion Entering the Compressor of an Air Vehicle P. Hendrick Université Libre de Bruxelles, ULB Avenue F.D. Roosevelt, 50 1050 Brussels BELGIUM patrick.hendrick@ulb.ac.be ABSTRACT One of the possible

More information

AIR EJECTOR WITH A DIFFUSER THAT INCLUDES BOUNDARY LAYER SUCTION

AIR EJECTOR WITH A DIFFUSER THAT INCLUDES BOUNDARY LAYER SUCTION Engineering MECHANICS, Vol. 20, 2013, No. 3/4, p. 213 220 213 AIR EJECTOR WITH A DIFFUSER THAT INCLUDES BOUNDARY LAYER SUCTION Václav Dvořák* The article deals with axial-symmetric subsonic air-to-air

More information

Wind Flow Validation Summary

Wind Flow Validation Summary IBHS Research Center Validation of Wind Capabilities The Insurance Institute for Business & Home Safety (IBHS) Research Center full-scale test facility provides opportunities to simulate natural wind conditions

More information

Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur

Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur Aircraft Design Prof. A.K Ghosh Department of Aerospace Engineering Indian Institute of Technology, Kanpur Lecture - 12 Design Considerations: Aerofoil Selection Good morning friends. The last lecture

More information

PHASE 1 WIND STUDIES REPORT

PHASE 1 WIND STUDIES REPORT PHASE 1 WIND STUDIES REPORT ENVIRONMENTAL STUDIES AND PRELIMINARY DESIGN FOR A SUICIDE DETERRENT SYSTEM Contract 2006-B-17 24 MAY 2007 Golden Gate Bridge Highway and Transportation District Introduction

More information

Performance Improvements in Boeing/AFOSR Mach 6 Quiet Wind Tunnel Based on CFD Predictions

Performance Improvements in Boeing/AFOSR Mach 6 Quiet Wind Tunnel Based on CFD Predictions Performance Improvements in Boeing/AFOSR Mach 6 Quiet Wind Tunnel Based on CFD Predictions Hadassah Naiman, Doyle D. Knight Rutgers University Selin Aradag US Air Force Academy Thomas J. Juliano,, Steven

More information

CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS

CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS Colloquium FLUID DYNAMICS 2008 Institute of Thermomechanics AS CR, v.v.i., Prague, October 22-24, 2008 p.1 CFD AND EXPERIMENTAL STUDY OF AERODYNAMIC DEGRADATION OF ICED AIRFOILS Vladimír Horák 1, Dalibor

More information

FABRICATION OF VERTICAL AXIS WIND TURBINE WITH WIND REDUCER AND EXPERIMENTAL INVESTIGATIONS

FABRICATION OF VERTICAL AXIS WIND TURBINE WITH WIND REDUCER AND EXPERIMENTAL INVESTIGATIONS 87 CHAPTER-4 FABRICATION OF VERTICAL AXIS WIND TURBINE WITH WIND REDUCER AND EXPERIMENTAL INVESTIGATIONS 88 CHAPTER-4 FABRICATION OF VERTICAL AXIS WIND TURBINE WITH WIND REDUCER AND EXPERIMENTAL INVESTIGATIONS

More information

Very Basic Design Considerations for Water-Bottle Rockets

Very Basic Design Considerations for Water-Bottle Rockets Very Basic Design Considerations for Water-Bottle Rockets The next few pages are provided to help in the design of your water-bottle rocket. Read through this packet and answer the questions on the last

More information

Research and optimization of intake restrictor for Formula SAE car engine

Research and optimization of intake restrictor for Formula SAE car engine International Journal of Scientific and Research Publications, Volume 4, Issue 4, April 2014 1 Research and optimization of intake restrictor for Formula SAE car engine Pranav Anil Shinde Mechanical Engineering,

More information

Physics: Principles and Applications, 6e Giancoli Chapter 3 Kinematics in Two Dimensions; Vectors. Conceptual Questions

Physics: Principles and Applications, 6e Giancoli Chapter 3 Kinematics in Two Dimensions; Vectors. Conceptual Questions Physics: Principles and Applications, 6e Giancoli Chapter 3 Kinematics in Two Dimensions; Vectors Conceptual Questions 1) Which one of the following is an example of a vector quantity? A) distance B) velocity

More information

Aerodynamic Terms. Angle of attack is the angle between the relative wind and the wing chord line. [Figure 2-2] Leading edge. Upper camber.

Aerodynamic Terms. Angle of attack is the angle between the relative wind and the wing chord line. [Figure 2-2] Leading edge. Upper camber. Chapters 2 and 3 of the Pilot s Handbook of Aeronautical Knowledge (FAA-H-8083-25) apply to powered parachutes and are a prerequisite to reading this book. This chapter will focus on the aerodynamic fundamentals

More information

Wind-Induced Oscillations Parametric Wind Tunnel Test

Wind-Induced Oscillations Parametric Wind Tunnel Test National Aeronautics and Space Administration Wind-Induced Oscillations Parametric Wind Tunnel Test Sam Yunis, Donald Keller, Thomas Ivanco, Jennifer Pinkerton NASA Langley Presented at Spacecraft and

More information

Series Environmental Chambers

Series Environmental Chambers 3119-600 Series Environmental Chambers Challenges in Non-Ambient Testing Testing at non-ambient temperatures adds another layer of challenges to your testing laboratory. Ensuring you get accurate and stable

More information

Chapter 3 EXPERIMENTAL: EQUIPMENT, SET-UP, AND PROCEDURE

Chapter 3 EXPERIMENTAL: EQUIPMENT, SET-UP, AND PROCEDURE Chapter 3 EXPERIMENTAL: EQUIPMENT, SET-UP, AND PROCEDURE 72 3.0 Introduction The experimental work was carried out in three stages. First stage: a laboratory scale single nozzle horizontal jet ejector

More information

AE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.

AE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability. Aerodynamics: Introduction Aerodynamics deals with the motion of objects in air. These objects can be airplanes, missiles or road vehicles. The Table below summarizes the aspects of vehicle performance

More information

FLOW VISUALIZATION TUNNEL

FLOW VISUALIZATION TUNNEL FLOW VISUALIZATION TUNNEL AEROLAB LLC 8291 Patuxent Range Road Suite 1200 Jessup, MD 20794 Phone: 301.776.6585 Fax: 301.776.2892 contact@aerolab.com www.aerolab.com TABLE OF CONTENTS Introduction 3 Description

More information

Effect of High-Lift Devices on Aircraft Wing

Effect of High-Lift Devices on Aircraft Wing IOSR Journal of Engineering (IOSRJEN) ISSN (e): 2250-3021, ISSN (p): 2278-8719 PP 01-05 www.iosrjen.org Effect of High-Lift Devices on Aircraft Wing Gaurav B. Mungekar 1, Swapnil N. More 1, Samadhan V.

More information

Takayuki Ieki. Introduction. Feature Article

Takayuki Ieki. Introduction. Feature Article F e a t u r e A r t i c l e Feature Article Development of a Large Capacity Liquid Vaporization System Using the Bubbling Method Achieving high accuracy through control of bubble diameter and liquid temperature

More information

Subsonic Wind Tunnel 300 mm

Subsonic Wind Tunnel 300 mm aerodynamics AF1300 TecQuipment s AF1300 Subsonic Wind Tunnel. See also AF300S starter set that includes AF1300Z Basic Lift and Drag Balance and a set of AF1300J Three Dimensional Drag Models with the

More information

CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS

CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS www.mechieprojects.com CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS PRESENTATION OUTLINE AIM INTRODUCTION LITERATURE SURVEY CFD ANALYSIS OF AEROFOIL RESULTS CONCLUSIONS www.mechieprojects.com

More information

External Tank- Drag Reduction Methods and Flow Analysis

External Tank- Drag Reduction Methods and Flow Analysis External Tank- Drag Reduction Methods and Flow Analysis Shaik Mohammed Anis M.Tech Student, MLR Institute of Technology, Hyderabad, India. G. Parthasarathy Associate Professor, MLR Institute of Technology,

More information

Materials: Balloon demo (optional): - balloon, string, drinking straw, flour (optional)

Materials: Balloon demo (optional): - balloon, string, drinking straw, flour (optional) Lesson Plan for Water Rockets Demonstration Concepts: Momentum, aerodynamics, propulsion Applicable Classes: EPSS 9, ASTR 3 Educational (for undergraduates) and Instructional (for TAs) videos available

More information

ROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)

ROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool) Unit D-1: Aerodynamics of 3-D Wings Page 1 of 5 AE301 Aerodynamics I UNIT D: Applied Aerodynamics ROAD MAP... D-1: Aerodynamics of 3-D Wings D-: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics

More information

ME 239: Rocket Propulsion. Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD

ME 239: Rocket Propulsion. Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD ME 239: Rocket Propulsion Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD 1 Commonly acting forces on a vehicle flying in a planetary atmosphere: Thrust Aerodynamic

More information

Development of Gasdynamic Probe for Total Temperature Measurement in gases

Development of Gasdynamic Probe for Total Temperature Measurement in gases ASET 20- National Conference on Emerging Trends in Propulsion Technology Development of Gasdynamic Probe for Total Temperature Measurement in gases K Sathiyamoorthy, Souren Misra 2, Srinivas J, Baskaran

More information

Theory of Flight Stalls. References: FTGU pages 18, 35-38

Theory of Flight Stalls. References: FTGU pages 18, 35-38 Theory of Flight 6.07 Stalls References: FTGU pages 18, 35-38 Review 1. What are the two main types of drag? 2. Is it possible to eliminate induced drag? Why or why not? 3. What is one way to increase

More information

Long Win s Educational Facilities for Fluid Mechanics

Long Win s Educational Facilities for Fluid Mechanics Since 1985 F luid mechanics is a science to study how fluids flow and how fluids act on objects. T he wind tunnel is a comprehensive, complete and substantial system for students to study fundamental and

More information

CFD Analysis of Giromill Type Vertical Axis Wind Turbine

CFD Analysis of Giromill Type Vertical Axis Wind Turbine 242 CFD Analysis Giromill Type Vertical Axis Wind Turbine K. Sainath 1, T. Ravi 2, Suresh Akella 3, P. Madhu Sudhan 4 1 Associate Pressor, Department Mechanical Engineering, Sreyas Inst. Engg. & Tech.,

More information

Characterizers for control loops

Characterizers for control loops Characterizers for control loops By: F. G. Shinskey (May 1999) Introduction Commercial controllers such as the PID series (proportional, integral, derivative, and their combinations) are linear devices

More information

Numerical Analysis of Wings for UAV based on High-Lift Airfoils

Numerical Analysis of Wings for UAV based on High-Lift Airfoils Numerical Analysis of Wings for UAV based on High-Lift Airfoils Sachin Srivastava Department of Aeronautical Engineering Malla Reddy College of Engineering & Technology, Hyderabad, Telangana, India Swetha

More information

Acceleration= Force OVER Mass. Design Considerations for Water-Bottle Rockets

Acceleration= Force OVER Mass. Design Considerations for Water-Bottle Rockets Acceleration= Force OVER Mass Design Considerations for Water-Bottle Rockets The next few pages are provided to help in the design of your water-bottle rocket. Read through this packet and answer the questions

More information

Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft

Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft , July 1-3, 2015, London, U.K. Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft Pooja Pragati, Sudarsan Baskar Abstract This paper provides a practical design of a new concept of massive

More information

Computational Analysis of Cavity Effect over Aircraft Wing

Computational Analysis of Cavity Effect over Aircraft Wing World Engineering & Applied Sciences Journal 8 (): 104-110, 017 ISSN 079-04 IDOSI Publications, 017 DOI: 10.589/idosi.weasj.017.104.110 Computational Analysis of Cavity Effect over Aircraft Wing 1 P. Booma

More information

Conceptual Design and Passive Stability of Tethered Platforms

Conceptual Design and Passive Stability of Tethered Platforms Conceptual Design and Passive Stability of Tethered Platforms Sara Smoot Advised by Ilan Kroo 1 Towed Bodies Definition: Two or more tethered objects immersed in a moving fluid. Aerostats Underwater towed

More information

RATE CONTROL SYSTEM FOR SOUNDING ROCKETS

RATE CONTROL SYSTEM FOR SOUNDING ROCKETS RATE CONTROL SYSTEM FOR SOUNDING ROCKETS Josef Ettl, Johann Pfänder German Aerospace Center (DLR), D-834 Wessling, Germany e-mail: josef.ettl@dlr.de johann.pfaender@dlr.de, 1. ABSTRACT DLR/Moraba has a

More information

Traffic circles. February 9, 2009

Traffic circles. February 9, 2009 Traffic circles February 9, 2009 Abstract The use of a traffic circle is a relatively common means of controlling traffic in an intersection. Smaller Traffic circles can be especially effective in routing

More information

SPH 4C Unit 4 Hydraulics and Pneumatic Systems

SPH 4C Unit 4 Hydraulics and Pneumatic Systems SPH 4C Unit 4 Hydraulics and Pneumatic Systems Properties of Fluids and Pressure Learning Goal: I can explain the properties of fluids and identify associated units. Definitions: Fluid: A substance that

More information

AIRFLOW GENERATION IN A TUNNEL USING A SACCARDO VENTILATION SYSTEM AGAINST THE BUOYANCY EFFECT PRODUCED BY A FIRE

AIRFLOW GENERATION IN A TUNNEL USING A SACCARDO VENTILATION SYSTEM AGAINST THE BUOYANCY EFFECT PRODUCED BY A FIRE - 247 - AIRFLOW GENERATION IN A TUNNEL USING A SACCARDO VENTILATION SYSTEM AGAINST THE BUOYANCY EFFECT PRODUCED BY A FIRE J D Castro a, C W Pope a and R D Matthews b a Mott MacDonald Ltd, St Anne House,

More information

Bottle Rockets. The bottle rocket, like the squid, uses water as the driving agent and compressed air instead of heat to provide the energy.

Bottle Rockets. The bottle rocket, like the squid, uses water as the driving agent and compressed air instead of heat to provide the energy. Bottle Rockets Problem/Purpose: To create a bottle rocket that will fly straight and will stay in the air for as long as possible. Background Information: A squid propels itself by filling its body with

More information

INVESTIGATION OF PRESSURE CONTOURS AND VELOCITY VECTORS OF NACA 0015IN COMPARISON WITH OPTIMIZED NACA 0015 USING GURNEY FLAP

INVESTIGATION OF PRESSURE CONTOURS AND VELOCITY VECTORS OF NACA 0015IN COMPARISON WITH OPTIMIZED NACA 0015 USING GURNEY FLAP INVESTIGATION OF PRESSURE CONTOURS AND VELOCITY VECTORS OF NACA 0015IN COMPARISON WITH OPTIMIZED NACA 0015 USING GURNEY FLAP 1 ANANTH S SHARMA, 2 SUDHAKAR S, 3 SWATHIJAYAKUMAR, 4 B S ANIL KUMAR 1,2,3,4

More information

A Performanced Based Angle of Attack Display

A Performanced Based Angle of Attack Display A Performanced Based Angle of Attack Display David F. Rogers, Phd, ATP www.nar-associates.com The Problem The current angle of attack displays basically warn you about the approach to stall with yellow

More information

Lesson: Airspeed Control

Lesson: Airspeed Control 11/20/2018 Airspeed Control Page 1 Lesson: Airspeed Control Objectives: o Knowledge o An understanding of the aerodynamics related to airspeed control o Skill o The ability to establish and maintain a

More information

Volume 2, Issue 5, May- 2015, Impact Factor: Structural Analysis of Formula One Racing Car

Volume 2, Issue 5, May- 2015, Impact Factor: Structural Analysis of Formula One Racing Car Structural Analysis of Formula One Racing Car Triya Nanalal Vadgama 1, Mr. Arpit Patel 2, Dr. Dipali Thakkar 3, Mr. Jignesh Vala 4 Department of Aeronautical Engineering, Sardar Vallabhbhai Patel Institute

More information

Experimental Analysis on Vortex Tube Refrigerator Using Different Conical Valve Angles

Experimental Analysis on Vortex Tube Refrigerator Using Different Conical Valve Angles International Journal of Engineering Research and Development e-issn: 7-067X, p-issn: 7-00X, www.ijerd.com Volume 3, Issue 4 (August ), PP. 33-39 Experimental Analysis on Vortex Tube Refrigerator Using

More information

ZIPWAKE DYNAMIC TRIM CONTROL SYSTEM OUTLINE OF OPERATING PRINCIPLES BEHIND THE AUTOMATIC MOTION CONTROL FEATURES

ZIPWAKE DYNAMIC TRIM CONTROL SYSTEM OUTLINE OF OPERATING PRINCIPLES BEHIND THE AUTOMATIC MOTION CONTROL FEATURES ZIPWAKE DYNAMIC TRIM CONTROL SYSTEM OUTLINE OF OPERATING PRINCIPLES BEHIND THE AUTOMATIC MOTION CONTROL FEATURES TABLE OF CONTENTS 1 INTRODUCTION 3 2 SYSTEM COMPONENTS 3 3 PITCH AND ROLL ANGLES 4 4 AUTOMATIC

More information

Design of a small-scaled de Laval nozzle for IGLIS experiment

Design of a small-scaled de Laval nozzle for IGLIS experiment Design of a small-scaled de Laval nozzle for IGLIS experiment Evgeny Mogilevskiy, R. Ferrer, L. Gaffney, C. Granados, M. Huyse, Yu. Kudryavtsev, S. Raeder, P. Van Duppen Instituut voor Kern- en Stralingsfysika,

More information

1. Which one of the following is a vector quantity? A. time B. speed C. energy D. displacement

1. Which one of the following is a vector quantity? A. time B. speed C. energy D. displacement 1. Which one of the following is a vector quantity? A. time B. speed C. energy D. displacement 2. A car is travelling at a constant speed of 26.0 m/s down a slope which is 12.0 to the horizontal. What

More information

EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES

EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES EXPERIMENTAL INVESTIGATION OF WAKE SURVEY OVER A CYLINDER WITH DIFFERENT SURFACE PROFILES Abdul Ahad Khan 1, Abhishek M. B 2, Tresa Harsha P George 3 1 Under Graduate student, Department of Aeronautical

More information

THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL. By Mehrdad Ghods

THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL. By Mehrdad Ghods THEORY OF WINGS AND WIND TUNNEL TESTING OF A NACA 2415 AIRFOIL By Mehrdad Ghods Technical Communication for Engineers The University of British Columbia July 23, 2001 ABSTRACT Theory of Wings and Wind

More information

Basic Fluid Mechanics

Basic Fluid Mechanics Basic Fluid Mechanics Chapter 7B: Forces on Submerged Bodies 7/26/2018 C7B: Forces on Submerged Bodies 1 Forces on Submerged Bodies Lift and Drag are forces exerted on an immersed body by the surrounding

More information

Gerald D. Anderson. Education Technical Specialist

Gerald D. Anderson. Education Technical Specialist Gerald D. Anderson Education Technical Specialist The factors which influence selection of equipment for a liquid level control loop interact significantly. Analyses of these factors and their interactions

More information

The Discussion of this exercise covers the following points:

The Discussion of this exercise covers the following points: Exercise 3-2 Orifice Plates EXERCISE OBJECTIVE In this exercise, you will study how differential pressure flowmeters operate. You will describe the relationship between the flow rate and the pressure drop

More information

Application of Simulation Technology to Mitsubishi Air Lubrication System

Application of Simulation Technology to Mitsubishi Air Lubrication System 50 Application of Simulation Technology to Mitsubishi Air Lubrication System CHIHARU KAWAKITA *1 SHINSUKE SATO *2 TAKAHIRO OKIMOTO *2 For the development and design of the Mitsubishi Air Lubrication System

More information

BUILD AND TEST A WIND TUNNEL

BUILD AND TEST A WIND TUNNEL LAUNCHING INTO AVIATION 9 2018 Aircraft Owners and Pilots Association. All Rights Reserved. UNIT 2 SECTION D LESSON 2 PRESENTATION BUILD AND TEST A WIND TUNNEL LEARNING OBJECTIVES By the end of this lesson,

More information

Aero Club. Introduction to Flight

Aero Club. Introduction to Flight Aero Club Presents Introduction to RC Modeling Module 1 Introduction to Flight Centre For Innovation IIT Madras Page2 Table of Contents Introduction:... 3 How planes fly How is lift generated?... 3 Forces

More information

Effect of Diameter on the Aerodynamics of Sepaktakraw Balls, A Computational Study

Effect of Diameter on the Aerodynamics of Sepaktakraw Balls, A Computational Study ISSN 1750-9823 (print) International Journal of Sports Science and Engineering Vol. 03 (2009) No. 01, pp. 017-021 Effect of Diameter on the Aerodynamics of Sepaktakraw Balls, A Computational Study Zahari

More information

AC : FORCE BALANCE DESIGN FOR EDUCATIONAL WIND TUNNELS

AC : FORCE BALANCE DESIGN FOR EDUCATIONAL WIND TUNNELS AC 2010-393: FORCE BALANCE DESIGN FOR EDUCATIONAL WIND TUNNELS Martin Morris, Bradley University Martin Morris is a professor of Mechanical Engineering at Bradley University in Peoria, IL. He worked for

More information

Stability and Flight Controls

Stability and Flight Controls Stability and Flight Controls Three Axes of Flight Longitudinal (green) Nose to tail Lateral (blue) Wing tip to Wing tip Vertical (red) Top to bottom Arm Moment Force Controls The Flight Controls Pitch

More information

The Estimation Of Compressor Performance Using A Theoretical Analysis Of The Gas Flow Through the Muffler Combined With Valve Motion

The Estimation Of Compressor Performance Using A Theoretical Analysis Of The Gas Flow Through the Muffler Combined With Valve Motion Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering The Estimation Of Compressor Performance Using A Theoretical Analysis Of The Gas Flow Through

More information

Aerodynamics of Winglet: A Computational Fluid Dynamics Study Using Fluent

Aerodynamics of Winglet: A Computational Fluid Dynamics Study Using Fluent Aerodynamics of : A Computational Fluid Dynamics Study Using Fluent Rohit Jain 1, Mr. Sandeep Jain, Mr. Lokesh Bajpai 1PG Student, Associate Professor, Professor & Head 1 Mechanical Engineering Department

More information

Numerical simulation and analysis of aerodynamic drag on a subsonic train in evacuated tube transportation

Numerical simulation and analysis of aerodynamic drag on a subsonic train in evacuated tube transportation Journal of Modern Transportation Volume 20, Number 1, March 2012, Page 44-48 Journal homepage: jmt.swjtu.edu.cn DOI: 10.1007/BF03325776 1 Numerical simulation and analysis of aerodynamic drag on a subsonic

More information

2. A car, starting from rest, accelerates in a straight-line path at a constant rate of 2.0 m/s 2. How far will the car travel in 12 seconds?

2. A car, starting from rest, accelerates in a straight-line path at a constant rate of 2.0 m/s 2. How far will the car travel in 12 seconds? Name: Date: 1. Carl Lewis set a world record for the 100.0-m run with a time of 9.86 s. If, after reaching the finish line, Mr. Lewis walked directly back to his starting point in 90.9 s, what is the magnitude

More information

XDF BURNERS DUAL FUEL EXCESS AIR BURNER FEATURES DESCRIPTION EXCESS AIR OPERATION

XDF BURNERS DUAL FUEL EXCESS AIR BURNER FEATURES DESCRIPTION EXCESS AIR OPERATION DUAL FUEL EXCESS AIR BURNER MODEL: 3610, 3651 Revision: 0 FEATURES Burns all fuel gases or light oils Nozzle mix design for on ratio control or excess air 350% excess air all sizes on gas or oil Turndown

More information

Designing a Model Rocket

Designing a Model Rocket Designing a Model Rocket Design Components In the following pages we are going to look at the design requirements for a stable single stage model rocket. From the diagram here you can see that the rocket

More information

Optimization of Ejector's Performance With a CFD Analysis. Amanda Mattos Karolline Ropelato Ricardo Medronho

Optimization of Ejector's Performance With a CFD Analysis. Amanda Mattos Karolline Ropelato Ricardo Medronho Optimization of Ejector's Performance With a CFD Analysis Amanda Mattos Karolline Ropelato Ricardo Medronho 2 Introduction Ejectors Equipment industrially used and based on the Venturi phenomena; With

More information

CHEMICAL ENGINEERING LABORATORY CHEG 239W. Control of a Steam-Heated Mixing Tank with a Pneumatic Process Controller

CHEMICAL ENGINEERING LABORATORY CHEG 239W. Control of a Steam-Heated Mixing Tank with a Pneumatic Process Controller CHEMICAL ENGINEERING LABORATORY CHEG 239W Control of a Steam-Heated Mixing Tank with a Pneumatic Process Controller Objective The experiment involves tuning a commercial process controller for temperature

More information

Motion Control of a Bipedal Walking Robot

Motion Control of a Bipedal Walking Robot Motion Control of a Bipedal Walking Robot Lai Wei Ying, Tang Howe Hing, Mohamed bin Hussein Faculty of Mechanical Engineering Universiti Teknologi Malaysia, 81310 UTM Skudai, Johor, Malaysia. Wylai2@live.my

More information

Design and Numerical Flow Analysis of Expansion Deflection Nozzle

Design and Numerical Flow Analysis of Expansion Deflection Nozzle Design and Numerical Flow Analysis of Expansion Deflection Nozzle Shaik Abdul Muwaaz 1, Nazumuddin Shaik 2 Post Graduate Student, Assistant Professor 1 Shaik Abdul Muwaaz, Aerospace Department, Nimra Institute

More information