# Level 7 Post Graduate Diploma in Mechanical Engineering Aerospace engineering

Save this PDF as:

Size: px
Start display at page:

## Transcription

1 Level 7 Post Graduate Diploma in Mechanical Engineering Aerospace engineering You should have the following for this examination one answer book non-programmable calculator pen, pencil, drawing instruments No additional data is attached General instructions This paper consists of nine questions. Answer any five questions. A non-programmable electronic calculator may be used but candidates must show sufficient steps to justify their answers. Drawings should be clear, in good proportion and in pencil. Do not use red ink. All questions carry equal marks. The maximum marks for each section within a question are shown. The City and Guilds of London Institute 2014 ST H1 PO

2 1 a) An aerofoil (NACA 4412) is mounted on an aircraft flying at an altitude of 3000 m. The characteristics of the aerofoil are shown in Figure Q1. Chord length of the aerofoil is 1.2 m. Determine i) the Lift per Unit Span, if the aircraft is flying at a speed of 50 m/s and the effective angle of attack is 4 degrees, ii) the minimum speed at which the aerofoil can produce lift per unit span of 3000 N/m. b) Compare and contrast incompressible flow from compressible flow. c) Explain the following terms. i) Critical Mach Number. (2 marks) ii) Aerodynamic Centre. (2 marks) d) Explain why a tapered wing is more likely to stall at the tip than a rectangular wing and describe why tip stall is a serious problem for an aircraft with an un-swept wing. Figure Q1 2

3 2 a) An elliptical orbit of a satellite is illustrated below in Figure Q2. Figure Q2 i) Redraw the Figure Q2 and identify the following parameters. 1. Semi-major axis 2. Radius of perigee 3. Radius of apogee 4. Major-axis ii) Calculate the eccentricity and Semi-Major axis of an orbit with a radius of perigee of 6600 km and a radius of apogee of km. b) During a typical mission, any spacecraft would encounter three environments. i) Name the three environments. (2 marks) ii) Selecting one of the three environments, explain the factors that the designer of the spacecraft must take into consideration to ensure the survival of the spacecraft. iii) A satellite is required to transfer from a lower earth orbit (LEO) with a particular inclination to a higher orbit with a different inclination. Explain a Hohmann Transfer Orbit and Inclination change manoeuvre that can be performed to achieve the new orbit. 3 a) Define Specific Impulse, I sp. Explain why it is desirable to use propellants with high I sp. b) A three stage rocket is used to send a 1000 kg payload into an orbit. Description about each stage is given in Table Q3. Stage Structure Mass (kg) Propellant Mass (kg) Propellant Type Specific Impulse (seconds) 1 6,000 60,000 LO 2 / RP I sp1 2 4,000 40,000 LO 2 / LK2 310 I sp2 3 2,000 20,000 N 1 O 4 / MMH 320 I sp3 Table Q3 The ideal burnout velocity is given by, m V BO = gi sp1 ln 1 m + gi sp2 ln 3 m + gi sp3 ln 5 m 2 m 4 m 6 where g gravitational force (9.81 ms 2 ) m 1, m 2 initial mass and final mass of stage 1 m 3, m 4 initial mass and final mass of stage 2 m 5, m 6 initial mass and final mass of stage 3 Find the ideal burnout velocity of the final stage. (10 marks) c) Outline the advantages and disadvantages of rockets with i) liquid propellant ii) solid propellant. 3 See next page

4 4 A four engine turbofan aircraft has the following characteristics: Mass kg Thrust 120 kn (From four engines) Wing Area 77 m 2 2 Drag Polar C L µ c l.ground roll 0.6 C L.max 2.0 a) Determine the initial acceleration and the acceleration when the aircraft is moving at 40 m/s. b) Estimate the distance required to reach a speed of 40 m/s. (If you could not solve part a), assume an acceleration of 3 m/s 2 for this part). c) Assume that an engine fails at a speed of 40 m/s. If the pilot takes 2 seconds to react and then brakes with a deceleration of 0.5g, determine the stopping distance. You may neglect acceleration during the reaction time. d) Briefly explain why aircraft use maximum flap setting during landing and not during takeoff. (5 marks) (5 marks) 5 a) i) Explain the formation of vortices with respect to a finite wing and describe how this affects lift and drag properties. ii) How do aspect ratio and elliptical lift distribution negate the effects of vortices? b) Describe the use of swept-back wings to increase the critical Mach number. (8 marks) 6 a) There are two types of aircraft navigation sensors, which are used in Inertial Navigation Systems (INS) and Global Navigation Satellite Systems (GNNS). Accelerometers and Gyros are the main INS sensors. Write a technical note on Accelerometers and Gyros among aircraft navigation sensing systems. (8 marks) b) Briefly explain the purpose and operation of i) Instrument Landing System (ILS) (3 marks) ii) Marker Beacon System. (3 marks) c) Name three other navigation aids available in the cockpit and explain how each helps in flight navigation. 7 a) Write the design objectives of a supersonic intake. b) There are essentially two primary types of options available for designing a supersonic intake, Normal Shock Diffusers and Oblique Shock Diffusers. Sketch them and discuss the advantages and disadvantages. c) A turboprop engine is selected for a general aviation aircraft. The drag when the aircraft is cruising at 70 m/s at an altitude of 2000 m is expected to be 950 N. i) Determine the required engine power if propeller efficiency is 85%. (2 marks) ii) Determine the fuel flow, if the Specific Fuel Consumption (SFC) is 60 µg/j. iii) The power is roughly proportional to the atmospheric density. Determine the sea level power, if the power required in part c) i) is at 2500 m altitude. 4

5 8 a) Explain the criterion for longitudinal static stability with the use of pitching moment variation with angle of incidence. b) i) Define the control fixed static stability condition. (2 marks) ii) With the information given in the graph below in Figure Q8 determine the control fixed neutral point. C L lift coefficient, η elevator angle, h centre of gravity. (2 marks) Figure Q8 c) i) Explain the two longitudinal dynamic stability modes and two of the three stability modes with the use of sketches. ii) Out of the following forces and moments identify the ones that describe lateral and directional dynamics. X Axial Force, Y Lateral Force, Z Normal Force, L Rolling Moment, M Pitching Moment, N Yawing Moment. (8 marks) 9 a) Explain how a pitot static tube is used to measure Equivalent Air Speed (EAS) and state why this speed measurement is called the EAS. b) Explain the primary and secondary effects of Aileron and Rudder. c) Explain why propeller engines are hardly used for large transport aircraft. (5 marks) d) Describe helicopter autorotation manoeuvre. (5 marks) 5

### CORE STANDARDS, OBJECTIVES, AND INDICATORS

Aerospace Engineering - PLtW Levels: 11-12 Units of Credit: 1.0 CIP Code: 14.0201 Core Code: 38-01-00-00-150 Prerequisite: Principles of Engineering, Introduction to Engineering Design Test: #967 Course

### If we let the vertical tail lift coefficient depend on a vertical tail lift curve slope and a rudder deflection we can write it as:

Roll and Yaw Moments and Stability Yaw Moment Equation The yaw moment is the moment about the z body axis and is positive if it moves the nose of the plane to the right. The big contributor to the yaw

### APPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1

APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane

### Propeller Fundamentals. A propeller is an interface between an engine and an aircraft. It creates thrust for flying an aircraft.

28 1 Propeller Fundamentals A propeller is an interface between an engine and an aircraft. It creates thrust for flying an aircraft. 2 Propeller blade 4-bladed propeller 3-bladed propeller 3 All propulsors

### Performance. 10. Thrust Models

Performance 10. Thrust Models In order to determine the maximum speed at which an aircraft can fly at any given altitude, we must solve the simple-looking equations for : (1) We have previously developed

### Lecture L17 - Orbit Transfers and Interplanetary Trajectories

S. Widnall, J. Peraire 16.07 Dynamics Fall 008 Version.0 Lecture L17 - Orbit Transfers and Interplanetary Trajectories In this lecture, we will consider how to transfer from one orbit, to another or to

### Section 4: The Basics of Satellite Orbits

Section 4: The Basics of Satellite Orbits MOTION IN SPACE VS. MOTION IN THE ATMOSPHERE The motion of objects in the atmosphere differs in three important ways from the motion of objects in space. First,

### Introduction to Aerospace Engineering Formulas

Introduction to Aerospace Engineering Formulas Aerodynamics Formulas. Definitions p = The air pressure. (P a = N/m 2 ) ρ = The air density. (kg/m 3 ) g = The gravitational constant. (Value at sea level

### CLASSIFICATION OF AIRCRAFT AND SPACECRAFT

TYPES OF AIRCRAFT CLASSIFICATION OF AIRCRAFT AND SPACECRAFT Aircraft can be classified into various types based on the mode of classification. In the following slide, a general classification of aircraft

### 6.1 AIRCRAFT TECHNICAL AND GENERAL AEROPLANE AIRFRAME AND SYSTEMS Fuselage. types of construction

6.1 IRCRFT TECHNICL ND GENERL EROPLNE 6.1.1 IRFRME ND SYSTEMS 6.1.1.1 Fuselage types of construction structural components and materials used stress 6.1.1.2 Cockpit and passenger cabin windows construction

### Forces on a Model Rocket

Forces on a Model Rocket This pamphlet was developed using information for the Glenn Learning Technologies Project. For more information, visit their web site at: http://www.grc.nasa.gov/www/k-12/aboutltp/educationaltechnologyapplications.html

### Performance. 15. Takeoff and Landing

Performance 15. Takeoff and Landing The takeoff distance consists of two parts, the ground run, and the distance from where the vehicle leaves the ground to until it reaches 50 ft (or 15 m). The sum of

### SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE. A thesis presented to. the faculty of

SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE A thesis presented to the faculty of the Russ College of Engineering and Technology of Ohio University In partial fulfillment of the requirement

### Chapter 6 Lateral static stability and control - 2 Lecture 20 Topics

Staility and control Chapter 6 Lateral static staility and control - Lecture Topics 6.1 Roll control 6.1.1 Aileron, diferential aileron and spoiler aileron 6.1. Rolling moment due to aileron 6.1.3 Damping

### Circular and Elliptical Orbit Geometries.

Circular and Elliptical Orbit Geometries. Satellite orbits ollow either circular or elliptical paths based on Keplers' laws o motion. Intrinsic assumptions are that the mass o the satellite is insigniicant

### APP Aircraft Performance Program Demo Notes Using Cessna 172 as an Example

APP Aircraft Performance Program Demo Notes Using Cessna 172 as an Example Prepared by DARcorporation 1. Program Layout & Organization APP Consists of 8 Modules, 5 Input Modules and 2 Calculation Modules.

### AE 430 - Stability and Control of Aerospace Vehicles

AE 430 - Stability and Control of Aerospace Vehicles Atmospheric Flight Mechanics 1 Atmospheric Flight Mechanics Performance Performance characteristics (range, endurance, rate of climb, takeoff and landing

### MAE 180A: Spacecraft Guidance I, Summer 2009 Final Exam Saturday, August 1st.

MAE 180A: Spacecraft Guidance I, Summer 2009 Final Exam Saturday, August 1st. Part I: Questions. (40pt) 8:00AM-8:35AM. Guidelines: Please turn in a neat and clean exam solution. Answers should be written

### Lecture L14 - Variable Mass Systems: The Rocket Equation

J. Peraire, S. Widnall 16.07 Dynamics Fall 2008 Version 2.0 Lecture L14 - Variable Mass Systems: The Rocket Equation In this lecture, we consider the problem in which the mass of the body changes during

### Introduction to Flight

Introduction to Flight Sixth Edition John D. Anderson, Jr. Curator for Aerodynamics, National Air and Space Museum Smithsonian Institution Professor Emeritus University of Maryland Boston Burr Ridge, IL

### air aerodynamics & flight vocabulary

TERM DEFINITION PICTURE OR CONNECTION Aerodynamics The science of moving through the air. Air Airfoil Air pressure Atmosphere An invisible mixture of gases, which make up earths atmosphere it consists

### Lab 8 Notes Basic Aircraft Design Rules 6 Apr 06

Lab 8 Notes Basic Aircraft Design Rules 6 Apr 06 Nomenclature x, y longitudinal, spanwise positions S reference area (wing area) b wing span c average wing chord ( = S/b ) AR wing aspect ratio C L lift

### DIRECCION DE PERSONAL AERONAUTICO DPTO. DE INSTRUCCION PREGUNTAS Y OPCIONES POR TEMA

MT DIREION DE PERSONL ERONUTIO DPTO. DE INSTRUION PREGUNTS Y OPIONES POR TEM Pag.: 1 TEM: 0114 TP - (HP. 03) ERODYNMIS OD_PREG: PREGUNT: RPT: 8324 When are inboard ailerons normally used? OPION : Low-speed

### Forces on the Rocket. Rocket Dynamics. Equation of Motion: F = Ma

Rocket Dynamics orces on the Rockets - Drag Rocket Stability Rocket Equation Specific Impulse Rocket otors Thrust orces on the Rocket Equation of otion: = a orces at through the Center of ass Center of

### AERODYNAMICS OF WING TIP SAILS

Journal of Engineering Science and Technology Vol. 1, No. 1 (2006) 89-98 School of Engineering, Taylor s College AERODYNAMICS OF WING TIP SAILS MUSHTAK AL-ATABI School of Engineering, Taylor s College

### Performance 4. Fluid Statics, Dynamics, and Airspeed Indicators

Performance 4. Fluid Statics, Dynamics, and Airspeed Indicators From our previous brief encounter with fluid mechanics we developed two equations: the one-dimensional continuity equation, and the differential

### Fundamentals of Airplane Flight Mechanics

Fundamentals of Airplane Flight Mechanics David G. Hull Fundamentals of Airplane Flight Mechanics With 125 Figures and 25 Tables 123 David G. Hull The University of Texas at Austin Aerospace Engineering

### F-104 Flight Controls

Information regarding the Lockheed F-104 Starfighter F-104 Flight Controls An article published in the Zipper Magazine #46 June-2001 Author: Country: Website: Email: Theo N.M.M. Stoelinga The Netherlands

### Principles of glider flight

Principles of glider flight [ Lift, drag & glide performance ] Richard Lancaster R.Lancaster@carrotworks.com ASK-21 illustrations Copyright 1983 Alexander Schleicher GmbH & Co. All other content Copyright

### Use the following information to deduce that the gravitational field strength at the surface of the Earth is approximately 10 N kg 1.

IB PHYSICS: Gravitational Forces Review 1. This question is about gravitation and ocean tides. (b) State Newton s law of universal gravitation. Use the following information to deduce that the gravitational

### Aircraft Design. Lecture 9: Stability and Control. G. Dimitriadis. Introduction to Aircraft Design

Aircraft Design Lecture 9: Stability and Control G. Dimitriadis Stability and Control Aircraft stability deals with the ability to keep an aircraft in the air in the chosen flight attitude. Aircraft control

### AOE 3104 Aircraft Performance Problem Sheet 2 (ans) Find the Pressure ratio in a constant temperature atmosphere:

AOE 3104 Aircraft Performance Problem Sheet 2 (ans) 6. The atmosphere of Jupiter is essentially made up of hydrogen, H 2. For Hydrogen, the specific gas constant is 4157 Joules/(kg)(K). The acceleration

### 2. Orbits. FER-Zagreb, Satellite communication systems 2011/12

2. Orbits Topics Orbit types Kepler and Newton laws Coverage area Influence of Earth 1 Orbit types According to inclination angle Equatorial Polar Inclinational orbit According to shape Circular orbit

### Wing Design: Major Decisions. Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist

Wing Design: Major Decisions Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist Wing Design Parameters First Level Span Area Thickness Detail Design

### The Purpose and Function of Airplane Parts

The Purpose and Function of Airplane Parts Warm-Up Questions CPS Questions 1-2 Lesson Overview How the fuselage and wing shape correspond to an aircraft s mission The types, purpose, and function of airfoil

### Aeroelasticity and Fuel Slosh!

Aeroelasticity and Fuel Slosh! Robert Stengel, Aircraft Flight Dynamics! MAE 331, 2014" Aerodynamic effects of bending and torsion" Modifications to aerodynamic coefficients" Dynamic coupling" Fuel shift

### 8 High Lift Systems and Maximum Lift Coefficients

8-1 8 High Lift Systems and Maximum Lift Coefficients In Section 7 the wing was examined with flaps retracted (clean wing). According to the assumptions from Section 5, the wing is, however, supposed to

### Effect of Propeller on Airplane Dynamics

Effect of Propeller on Airplane Dynamics The propeller creates considerable unfavorable forces that need to be trimmed out to keep the airplane flying in a desirable manner. Many airplanes are rigged to

### FUNDAMENTALS OF AERODYNAMICS

TRAINEE GUIDE FOR PREFLIGHT C-9B-0020 Unit 1 FUNDAMENTALS OF AERODYNAMICS Prepared by NAVAL AVIATION SCHOOLS COMMAND 181 CHAMBERS AVE SUITE C PENSACOLA, FL 32508 Prepared for CENTER FOR NAVAL AVIATION

### Chapter 5 Directional static stability and control - 3 Lecture 18 Topics

Chapter 5 Directional static stability and control - 3 Lecture 18 Topics 5.8.3 Control in asymmetric power, steady flight after engine failure and minimum control speed Example 5.3 5.8.4 Control for spin

### Learning Objectives 5.1 PRINCIPLES OF FLIGHT: aeroplane

080 00 00 00 PRINCIPLES OF FLIGHT 081 00 00 00 PRINCIPLES OF FLIGHT AEROPLANE 081 01 00 00 SUBSONIC AERODYNAMICS 081 01 01 00 Basics, laws and definitions 081 01 01 01 Laws and definitions LO - List the

### ExpressJet Airlines Pilot Job Knowledge Test Outline

ExpressJet Airlines Pilot Job Knowledge Test Outline The job knowledge test administered as part of the pilot interview process consists of questions in four major knowledge areas essential to piloting

### Development of models for high precision simulation of the space mission MICROSCOPE

Development of models for high precision simulation of the space mission MICROSCOPE Stefanie Bremer Meike List Hanns Selig Claus Lämmerzahl Outline The space mission MICROSCOPE High Performance Satellite

### ESTIMATING R/C MODEL AERODYNAMICS AND PERFORMANCE

ESTIMATING R/C MODEL AERODYNAMICS AND PERFORMANCE Adapted from Dr. Leland M. Nicolai s Write-up (Technical Fellow, Lockheed Martin Aeronautical Company) by Dr. Murat Vural (Illinois Institute of Technology)

### Principles of Flight. There are four major forces acting on an aircraft: Gravity Lift Drag Thrust. lift. thrust. drag. gravity

Principles of Flight There are four major forces acting on an aircraft: Gravity Lift Drag Thrust Gravity Gravity is the downward force that keeps the airplane on the ground or pulls the airplane toward

### Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics

Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics 6.11 General discussions on control surface 6.11.1 Aerodynamic balancing 6.11.2 Set back hinge or over hang balance 6.11.3 Horn balanace

### Does currently available technology have the capacity to facilitate a manned mission to Mars?

Furze Platt Senior School Does currently available technology have the capacity to facilitate a manned mission to Mars? Daniel Messias Date: 8/03/2015 Candidate Number: 7158 Centre Number: 51519 Contents

### Flight Controls. Control The Wright Brothers described flight in three axes roll, pith and yaw.

Flight Controls The Wright Brothers were engineers first, pilots second. Introduction We have learned about the four forces that act on an airplane. The Wright Brothers were the first to fly because they

### GATE 2012 Online Examination AE : AEROSPACE ENGINEERING Duration: Three Hours Maximum Marks: 100

GATE 0 Online Examination AE : AEROSPACE ENGINEERING Duration: Three Hours Maximum Marks: 00 Read the following instructions carefully.. The computer allotted to you at the examination center runs a specialized

### Compute the average effective exhaust velocity for the propulsion system as a whole and from this also the average specific impulse.

2 2.1 Ariane 5 Thrust Initially at lift-off of an ARIANE 5 launch vehicle two P230 solid propellant boosters plus the main Vulcain engine are ignited. The two different components of the launch vehicle

### Cefiro: An Aircraft Design Project in the University of Seville

Cefiro: An Aircraft Design Project in the University of Seville Carlos Bernal Ortega, Andrés Fernández Lucena, Pedro López Teruel, Adrián Martín Cañal, Daniel Pérez Alcaraz, Francisco Samblás Carrasco

### AOE 3134 Complete Aircraft Equations

AOE 3134 Complete Aircraft Equations The requirements for balance and stability that we found for the flying wing carry over directly to a complete aircraft. In particular we require the zero-lift pitch

### Orbital Mechanics. Angular Momentum

Orbital Mechanics The objects that orbit earth have only a few forces acting on them, the largest being the gravitational pull from the earth. The trajectories that satellites or rockets follow are largely

### Q. 1 Q. 5 carry one mark each.

GATE 016 General Aptitude GA Set-8 Q. 1 Q. 5 carry one mark each. Q.1 The chairman requested the aggrieved shareholders to him. (A) bare with (B) bore with (C) bear with (D) bare Q. Identify the correct

### Understanding the motion of the Universe. Motion, Force, and Gravity

Understanding the motion of the Universe Motion, Force, and Gravity Laws of Motion Stationary objects do not begin moving on their own. In the same way, moving objects don t change their movement spontaneously.

### ASYMMETRIC FLIGHT INTRODUCTION

ASYMMETRIC FLIGHT INTRODUCTION This section provides a discussion of the asymmetric flight of multi-engine airplanes following loss of power from an engine(s) mounted laterally either side of the centerline.

### Name Class Period. F = G m 1 m 2 d 2. G =6.67 x 10-11 Nm 2 /kg 2

Gravitational Forces 13.1 Newton s Law of Universal Gravity Newton discovered that gravity is universal. Everything pulls on everything else in the universe in a way that involves only mass and distance.

### SIMPLIFIED METHOD FOR ESTIMATING THE FLIGHT PERFORMANCE OF A HOBBY ROCKET

SIMPLIFIED METHOD FOR ESTIMATING THE FLIGHT PERFORMANCE OF A HOBBY ROCKET WWW.NAKKA-ROCKETRY.NET February 007 Rev.1 March 007 1 Introduction As part of the design process for a hobby rocket, it is very

### CHAPTER 1. Fundamental Mathematics

Volume 9 Performance (JAR Ref 032) Table of Contents CHAPTER 1 Fundamental Mathematics Introduction...1-1 Equations...1-1 The Principle of an Equation...1-1 Transposing Equations...1-1 Adding and Subtracting...1-1

### 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,

### Penn State University Physics 211 ORBITAL MECHANICS 1

ORBITAL MECHANICS 1 PURPOSE The purpose of this laboratory project is to calculate, verify and then simulate various satellite orbit scenarios for an artificial satellite orbiting the earth. First, there

### Performance. Power Plant Output in Terms of Thrust - General - Arbitrary Drag Polar

Performance 11. Level Flight Performance and Level flight Envelope We are interested in determining the maximum and minimum speeds that an aircraft can fly in level flight. If we do this for all altitudes,

### Louisiana Tech University Flight Operations Cessna 172 VFR Profiles

PURPOSE Louisiana Tech University Flight Operations Cessna 172 VFR Profiles The information contained herein has been developed for the purpose of compliance with 14 CFR 141.85. The main objective of this

### General aviation & Business System Level Applications and Requirements Electrical Technologies for the Aviation of the Future Europe-Japan Symposium

General aviation & Business System Level Applications and Requirements Electrical Technologies for the Aviation of the Future Europe-Japan Symposium 26 March 2015 2015 MITSUBISHI HEAVY INDUSTRIES, LTD.

### High-Lift Systems. High Lift Systems -- Introduction. Flap Geometry. Outline of this Chapter

High-Lift Systems Outline of this Chapter The chapter is divided into four sections. The introduction describes the motivation for high lift systems, and the basic concepts underlying flap and slat systems.

### Date: 30 September East of Frankfurt/Main. Manufacturer / Model: Boeing / B

Bundesstelle für Flugunfalluntersuchung German Federal Bureau of Aircraft Accident Investigation Factual Report The Investigation Report was written in accordance with para 18 of the Law Relating to the

### Collaborative UAV Study. Tan Han Rong, Ronald

Collaborative UAV Study Tan Han Rong, Ronald Department of Mechanical Engineering, National University of Singapore ABSTRACT This is a preliminary assessment into the feasibility of developing a UAV that

### Form And Function What Is Angle of Attack? By Ed Kolano

Form And Function What Is Angle of Attack? By Ed Kolano To new pilots with a military inclination, angle of attack might be another way to describe a military flanking maneuver. But the context here is

### Requirements to servo-boosted control elements for sailplanes

Requirements to servo-boosted control elements for sailplanes Aerospace Research Programme 2004 A. Gäb J. Nowack W. Alles Chair of Flight Dynamics RWTH Aachen University 1 XXIX. OSTIV Congress Lüsse, 6-136

### Summary. Engine Sizing & Selection. Propulsion Integration Extremely Important. Airframe Integrator s Motto. Piston Engine.

Engine Sizing & Selection Copyright 2006 by Don Edberg Summary Engine Sizing & Arrangement Introduction Performance Requirements Engine Geometric Characteristics & Placement Airframe Integrator s Motto

### RS platforms. Fabio Dell Acqua - Gruppo di Telerilevamento

RS platforms Platform vs. instrument Sensor Platform Instrument The remote sensor can be ideally represented as an instrument carried by a platform Platforms Remote Sensing: Ground-based air-borne space-borne

### A Sounding Rocket Launch Technique For Pico Satellite Payloads. Mark S. Goll and David W. Dunham Texas Rocket Company and Kinetx Inc.

A Sounding Rocket Launch Technique For Pico Satellite Payloads Mark S. Goll and David W. Dunham Texas Rocket Company and Kinetx Inc. Texas Rocket Company 19785 Marbach Lane San Antonio, Texas 78266 ABSTRACT

### ANGARA 1. IDENTIFICATION. 1.1 Name. 1.2 Classification. Family : ANGARA Series : ANGARA Version : ANGARA 1.1

1. IDENTIFICATION 1.1 Name 1.2 Classification Family : Series : Version : 1.1 Category : SPACE LAUNCH VEHICLE Class : Small Launch Vehicle (SLV) Type : Expendable Launch Vehicle (ELV) 1.3 Manufacturer

### Cessna Skyhawk II / 100. Performance Assessment

Cessna Skyhawk II / 100 Performance Assessment Prepared by John McIver B.Eng.(Aero) Temporal Images 23rd January 2003 http://www.temporal.com.au Cessna Skyhawk II/100 (172) Performance Assessment 1. Introduction

### Can Hubble be Moved to the International Space Station? 1

Can Hubble be Moved to the International Space Station? 1 On January 16, NASA Administrator Sean O Keefe informed scientists and engineers at the Goddard Space Flight Center (GSFC) that plans to service

### A Shuttle Flight LAUNCH!

The Space Shuttle 1 LAUNCH! The Space Shuttle is launched from the Kennedy Space Center at Cape Canaveral, Florida. A Shuttle flight takes months of careful preparation. Each launch is preceded by a countdown,

### Aircraft Theory of Flight and Operation

Aircraft Theory of Flight and Operation Unit: 1 Content Standard(s) and Safety 1. Apply safety rules, regulations, and procedures for the Aviation Technology program, including safety concerns in the areas

### Orbital Dynamics: Formulary

Orbital Dynamics: Formulary 1 Introduction Prof. Dr. D. Stoffer Department of Mathematics, ETH Zurich Newton s law of motion: The net force on an object is equal to the mass of the object multiplied by

### Light Aircraft Design

New: Sport Pilot (LSA) The Light Aircraft Design Computer Program Package - based on MS-Excelapplication was now extented with the new Sport Pilots (LSA) loads module, which includes compliance for the

### Credit value: 10 Guided learning hours: 60

Unit 66: Theory of Flight Unit code: QCF Level 3: Credit value: 10 Guided learning hours: 60 Aim and purpose A/600/7123 BTEC Nationals This unit will provide learners with an understanding of the atmosphere

### AIRBORNE ANALYTICAL FLIGHT RISK CONTROL SYSTEM FOR HELICOPTERS

Latest Research and Development Projects INSTITUTE FOR RISK PROBLEMS (IPR) AIRBORNE ANALYTICAL FLIGHT RISK CONTROL SYSTEM FOR HELICOPTERS Contact information: 5, K. Marksa st., Ramenskoye, Moscow Region,

### IN FLIGHT MANEUVERS AND OPERATING PROCEDURES C-172

Flight Training and Aircraft Rentals 14150 14532 SW 129th St. MIAMI, FL. 33186 www.flymiami.com 305-259-5611 IN FLIGHT MANEUVERS AND OPERATING PROCEDURES C-172 Normal Cruise: Straight and level flight

### WIND ENERGY SYSTEMS Weeks 12

ENGG378/948 Sustainable Energy Technologies WIN ENERGY SYSTEMS Weeks Theory of horizontal axis wind turbine (HAWT) Airfoils erivation of Blade Element Momentum Theory Solution procedure Objectives of lecture

### LEADER GUIDE for MODULE ONE

LEADER GUIDE for MODULE ONE INTRODUCTION TO FLIGHT Chapter One Flight Learning Outcomes--Upon completion of this chapter, the cadet should know: The relationship between Bernoulli s Principle, Newton s

### Rocket Principles. Rockets: A Teacher's Guide with Activities in Science, Mathematics, and Technology EG-108 February Outside Air Pressure

Rocket Principles Outside ir Pressure Inside ir Pressure ir Moves Balloon Moves rocket in its simplest form is a chamber enclosing a gas under pressure. small opening at one end of the chamber allows the

### Ideal Jet Propulsion Cycle

Ideal Jet ropulsion Cycle Gas-turbine engines are widely used to power aircrafts because of their light-weight, compactness, and high power-to-weight ratio. Aircraft gas turbines operate on an open cycle

### Gas Turbine Engine Performance Analysis. S. Jan

Gas Turbine Engine Performance Analysis S. Jan Jul. 21 2014 Chapter 1 Basic Definitions Potential & Kinetic Energy PE = mgz/g c KE = mv 2 /2g c Total Energy Operational Envelopes & Standard Atmosphere

### A MONTE CARLO DISPERSION ANALYSIS OF A ROCKET FLIGHT SIMULATION SOFTWARE

A MONTE CARLO DISPERSION ANALYSIS OF A ROCKET FLIGHT SIMULATION SOFTWARE F. SAGHAFI, M. KHALILIDELSHAD Department of Aerospace Engineering Sharif University of Technology E-mail: saghafi@sharif.edu Tel/Fax:

### Building Planetary Orbits (the Feynman way)

Building Planetary Orbits (the Feynman way) Using a method of computing known as finite differences we can quickly calculate the geometry of any planetary orbit. All we need are a starting position and

### Fluid Mechanics Prof. S. K. Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur

Fluid Mechanics Prof. S. K. Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur Lecture - 20 Conservation Equations in Fluid Flow Part VIII Good morning. I welcome you all

### Design and Structural Analysis of the Ribs and Spars of Swept Back Wing

Design and Structural Analysis of the Ribs and Spars of Swept Back Wing Mohamed Hamdan A 1, Nithiyakalyani S 2 1,2 Assistant Professor, Aeronautical Engineering & Srinivasan Engineering College, Perambalur,

### The Four Fundamental Flight Maneuvers: by: Darryl Kalthof c2010

The Four Fundamental Flight Maneuvers: by: Darryl Kalthof www.bayareaflyinglessons.com c2010 Note you will get even more out of this file if you read a chapter on aerodynamics first! Elements: Effect and

### NACA Nomenclature NACA 2421. NACA Airfoils. Definitions: Airfoil Geometry

0.40 m 0.21 m 0.02 m NACA Airfoils 6-Feb-08 AE 315 Lesson 10: Airfoil nomenclature and properties 1 Definitions: Airfoil Geometry z Mean camber line Chord line x Chord x=0 x=c Leading edge Trailing edge

### Content must not be changed in any way or reproduced in any format or medium without the formal permission of the copyright holder(s)

nn Ferguson, K., and Thomson, D. (2015) Performance comparison between a conventional helicopter and compound helicopter configurations. Proceedings of the Institution of Mechanical Engineers, Part G:

### At What True Anomaly Should I Perform a Burn If I Want To Minimize Fuel Usage?

At What True Anomaly Should I Perform a Burn If I Want To Minimize Fuel Usage? In this exercise you will create a scenario that will help you change the orbit of a satellite that is not at the proper altitude.

### 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

### State Newton's second law of motion for a particle, defining carefully each term used.

5 Question 1. [Marks 20] An unmarked police car P is, travelling at the legal speed limit, v P, on a straight section of highway. At time t = 0, the police car is overtaken by a car C, which is speeding