©M. S. Ramaiah University of Applied Science 1 lty of Engineering & Technology Module Code: ACD505 Module Title: Aircraft Performance and Flight Dynamics Module Leaders: M. Sivapragasam and Dr. H. K. Narahari
ACD505 Session 00
Jul 17, 2016
Thrust is the force which moves any aircraft through the air. Propulsion system is the machine that produces thrust to push the aircraft forward through air. Different propulsion systems develop thrust in different ways, but all thrust is generated through some application of Newton's third law of motion. A gas (working fluid) is accelerated by the engine, and the reaction to this acceleration produces the thrust force. Further, the type of power plant to be used in the aircraft depends on four important factors, namely: the aircraft mission, over all weight, flying range and endurance and altitude of flight.
This assignment work was partitioned into three different parts (A, B and C respectively). In Part-A, a debate was made on the viability of implementation of twin engine propulsion system for long range civil aircrafts. Logical arguments based on literatures collected from various internet and text book sources were made and the conclusion of the usage of twin engine propulsion system for long range civil aircrafts was drawn. In Part-B, for the given mission of the aircraft, suitable power plant was chosen (Turbo fan engine) and corresponding cycle analysis calculations was done. The calculations were repeated for a range of flying altitudes and performance plots drawn were critically examined. Also, for the given Turbo prop engine data, cycle analysis calculations were done. The calculations were repeated for a set of Mach numbers and performance plots drawn were critically examined. The different engine installation techniques for a turboprop engine was also discussed. In Part-C, flow over an axial gas turbine cascade was analysed in Ansys-FLUENT software package. The blade geometry was created in Ansys-BladeGen and then imported to CATIA to create the flow domain. Meshing of the geometry was done in Fluent-ICEMCFD.
The total momentum thrust and propulsion efficiency for the selected turbofan engine for the extreme altitudes of 4km & 18km was estimated as 73541N & 9375N and 47% & 40% respectively. The percentage of cold thrust generated at 4km & 18km was 60% & 45% respectively. Both momentum thrust and propulsion efficiency of the engine was observed to decrease with increase in altitude. The propeller thrust and power for the given turboprop engine for flight Mach corresponding to 0.1 & 0.8 was estimated to be 191669N & 25546N and 6074467W & 6477144W respectively. With increasing Mach number of flight, propeller thrust and power was observed to decrease and increase respectively. For the flow analysis over the axial turbine cascade, maximum static pressure value occurs for +150 (2.67*105 Pa) and minimum for 00 (2.5*105 Pa) flow incidence angles respectively. The maximum Mach number value occurs for +150 (1.89) and minimum for -150 (1.57) flow incidence angles respectively. Further the pressure loss was observed to be minimum for -150 (0.1118) flow incidence angle and maximum for +150 (0.2538) flow incidence angle.
This assignment work was partitioned into three different parts (A, B and C respectively). In Part-A, a debate was made on the viability of implementation of twin engine propulsion system for long range civil aircrafts. Logical arguments based on literatures collected from various internet and text book sources were made and the conclusion of the usage of twin engine propulsion system for long range civil aircrafts was drawn. In Part-B, for the given mission of the aircraft, suitable power plant was chosen (Turbo fan engine) and corresponding cycle analysis calculations was done. The calculations were repeated for a range of flying altitudes and performance plots drawn were critically examined. Also, for the given Turbo prop engine data, cycle analysis calculations were done. The calculations were repeated for a set of Mach numbers and performance plots drawn were critically examined. The different engine installation techniques for a turboprop engine was also discussed. In Part-C, flow over an axial gas turbine cascade was analysed in Ansys-FLUENT software package. The blade geometry was created in Ansys-BladeGen and then imported to CATIA to create the flow domain. Meshing of the geometry was done in Fluent-ICEMCFD.
The total momentum thrust and propulsion efficiency for the selected turbofan engine for the extreme altitudes of 4km & 18km was estimated as 73541N & 9375N and 47% & 40% respectively. The percentage of cold thrust generated at 4km & 18km was 60% & 45% respectively. Both momentum thrust and propulsion efficiency of the engine was observed to decrease with increase in altitude. The propeller thrust and power for the given turboprop engine for flight Mach corresponding to 0.1 & 0.8 was estimated to be 191669N & 25546N and 6074467W & 6477144W respectively. With increasing Mach number of flight, propeller thrust and power was observed to decrease and increase respectively. For the flow analysis over the axial turbine cascade, maximum static pressure value occurs for +150 (2.67*105 Pa) and minimum for 00 (2.5*105 Pa) flow incidence angles respectively. The maximum Mach number value occurs for +150 (1.89) and minimum for -150 (1.57) flow incidence angles respectively. Further the pressure loss was observed to be minimum for -150 (0.1118) flow incidence angle and maximum for +150 (0.2538) flow incidence angle.
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©M. S. Ramaiah University of Applied Sciences
1Faculty of Engineering & Technology
Module Code: ACD505
Module Title: Aircraft Performance and Flight Dynamics
Module Leaders:
M. Sivapragasam and Dr. H. K. Narahari
©M. S. Ramaiah University of Applied Sciences
2Faculty of Engineering & Technology
Module Details
• Course: M. Tech. in ACD• Department: Automotive & Aeronautical Engineering• Head of the Department: Dr. S. Srikari ([email protected]) • Faculty: Engineering & Technology• Dean: Prof. H. K. Narahari ([email protected])
©M. S. Ramaiah University of Applied Sciences
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Why this ModuleThe objectives of the course are to enable the students to:1. Explain the construction, working principles and functional requirements of aircraft systems with respect to their performance2. Convert the customer requirements to viable design specifications and evolve
conceptual design3. Model, simulate, analyse and validate aircraft conceptual design to meet
operational requirements using commercially available tools4. Demonstrate Critical, analytical, problem solving and research skills in the domain
of Aeronautical Engineering5. Develop a career in Aeronautical Engineering6. Practise Teamwork, lifelong learning and continuous improvementThe module is being delivered to meet the above highlighted objectives of the course.
©M. S. Ramaiah University of Applied Sciences
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Module Aim and SummaryThis module intends to prepare students for evaluating the stability and control parameters of an aircraft using linear methods. Students are taught basics of static stability and control for the following modes: longitudinal, lateral and directional. Students are taught dynamical equations governing the motion of aircraft in space. They are trained to solve linearised equations of motion and compute stability margins.
©M. S. Ramaiah University of Applied Sciences
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Module Intended Learning OutcomesAfter undergoing this module students will be able to:
1. Explain the influence of aerodynamic characteristics, weight, engine performance and flight altitude on the aircraft performance
2. Distinguish performance requirements between different class of aircraft
3. Analyse and evaluate aeroplane performance for different phases of flight, Level flight, Turning, Gliding, climb, takeoff and landing through solution of available standard mathematical models
4. Calculate size and evaluate control surfaces using standard correlations
5. Critically evaluate the stability derivatives and establish flight boundaries such as range and endurance, payload range, V n ‐ ‐diagram and turn performance
©M. S. Ramaiah University of Applied Sciences
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Indicative ContentSystems of axes and notation: Earth, body axes, Euler angles and transformations
Stability and Control : Static equilibrium and trim, wing location, tail plane sizing, CG travel,
Longitudinal : Stability : Sizing of Controls surfaces Neutral Point : Stick Fixed and Free
Lateral and Directional Stability : Coupling between the two , Sizing of Controls surfaces
Equations of motion of a rigid aircraft in space: Linearisations , flat earth simplifications.
Decoupled equations
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Indicative ContentSolution techniques: State space approach, Matrix methods, Transfer function
Longitudinal Dynamics : Modes of a typical Aircraft, Short period, long period
Lateral and directional dynamics : Modes of a typical Aircraft, rolling, Dutch, spiral
Stability and control derivatives turning flight: Turning flight in general, Maximum load
factor and bank angle, Fastest and tightest turn, sustained and attained turn rates, V-n
Diagram
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Teaching and Learning Methods
• Lecture Sessions• Laboratory practice
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Method of AssessmentA module assessment will have two components: Component - 1: 50% weight Assignment (30% weight) followed by a presentation on the assignment (10% weight) and a laboratory examination (10% weight). A word processed assignment is to be submitted followed by a presentation by the students. • In case there is no laboratory examination, the assignment (40% weight) followed by a presentation on the assignment (10% weight) - applicable only for those modules where it is not possible to have laboratory examination.
Component - 2 : 50% weight • Written Examination (50% weight).
©M. S. Ramaiah University of Applied Sciences
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Method of Assessment Contd.. The assessment questions are set to test the learning outcomes. In each component certain learning outcomes are assessed. The following table illustrates the focus of learning outcome in each component assessed:
Both components will be moderated by a second examiner.A student is required to score a minimum of 40% in each of the components and an overall 40% for successful completion of a module and earning the credits.
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Software tool and Resources
• MATLAB• Piano-X
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Module DeliveryTheory• M. Sivapragasam• Dr. H. K. Narahari
Practice• Mr. M. Sivapragasam
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Referencesa. Essential Reading
1. Class Notes2. M.V. Cook. Flight Dynamics Principles, 2nd Edition, 2007, Elsevier3. J.B. Russel, Performance and Stability of Aircraft,2003, Butterworth
b. Recommended Reading:1. Ashish Tewari. (2007) Atmospheric and Space Flight Dynamics- Modeling and Simulationwith MATLAB and Simulink, 2007, Birkhauser2. Ilan Kroo Aircraft Design: Synthesis and Analysis, 20113. John D. Anderson. (1999) Aircraft Performance and Design, McGraw-Hill4. Nelson, R.C. (1998) Flight Stability and Automatic Control, 2nd Edition, McGraw Hill5. AIAA Aerospace Design Engineers Guide, 2003, 5th Edition
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Module Delivery Schedule (Theory) Session
No.Date Time Day Topic Delivered By Additional
Activity
1 01-06-2015 09:30 AM -1:00 PM Monday Aircraft Steady and Level Flight-1 M. Sivapragasam
2 02-06-2015 09:30 AM -1:00 PM
TuesdayAircraft Steady and Level Flight-2 M. Sivapragasam
3 03-06-2015 09:30 AM -1:00 PM
Wednesday Aircraft Accelerated Flight-1M. Sivapragasam
4 04-06-2015 09:30 AM -1:00 PM
Thursday Aircraft Accelerated Flight-2M. Sivapragasam
5 05-06-2015 09:30 AM -1:00 PM
FridayAircraft Equilibrium, Stability and Control M. Sivapragasam
6 08-06-2015 09:30 AM -1:00 PM Monday Aircraft Longitudinal Static Stability M. Sivapragasam
7 09-06-2015 09:30 AM -1:00 PM
TuesdayAircraft Lateral Static Stability M. Sivapragasam
8 10-06-2015 09:30 AM -1:00 PM
WednesdayAircraft Manoeuvrability M. Sivapragasam
9 11-06-2015 09:30 AM -1:00 PM
ThursdayAircraft Flight Dynamics - 1
Dr. H. K. Narahari
10 12-06-2015 09:30 AM -1:00 PM
FridayAircraft Flight Dynamics - 2
Dr. H. K. Narahari
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Module Delivery Schedule (Laboratory) Session
No.Date Time Day Topic Delivered By Additional
Activity
1 01-06-2015 2:00 PM -5:30 PM Monday Performance calculations using MATLAB M. Sivapragasam
2 02-06-2015 2:00 PM -5:30 PM
TuesdayPerformance calculations using MATLAB M. Sivapragasam
3 03-06-2015 2:00 PM -5:30 PM
WednesdayPerformance calculations using MATLAB M. Sivapragasam
4 04-06-2015 2:00 PM -5:30 PM
ThursdayPerformance calculations using MATLAB M. Sivapragasam
5 05-06-2015 2:00 PM -5:30 PM
FridayPerformance calculations using MATLAB M. Sivapragasam
6 08-06-2015 2:00 PM -5:30 PM Monday Performance calculations using Piano-X M. Sivapragasam
7 09-06-2015 2:00 PM -5:30 PM
TuesdayPerformance calculations using Piano-X M. Sivapragasam
8 10-06-2015 2:00 PM -5:30 PM
WednesdayStatic stability calculations using MATLAB M. Sivapragasam
9 11-06-2015 2:00 PM -5:30 PM
ThursdayStatic stability calculations using MATLAB
M. Sivapragasam
10 12-06-2015 2:00 PM -5:30 PM
FridayDynamic stability calculations using MATLAB M. Sivapragasam
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Theory Sessions
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Session No. 1Aircraft Steady and Level Flight – 1
At the end of this session, students will be able to :• Explain the absolute and functional performance of an aircraft• List the crucial aircraft and propulsion parameters influencing the
performance characteristics of an aircraft• Show the forces acting on an aircraft in steady level flight and derive the
equations of motion• Calculate the thrust required and available for steady level flight for jet
aircraft• Calculate the power required and available for steady level flight for
propeller-driven aircraft• Assess the importance of maximum velocity on aircraft design
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At the end of the session, students will be able to :• Differentiate range and endurance• Calculate the range and endurance of a propeller-driven aircraft• Calculate the range and endurance of a jet aircraft• Apply the Breguet equations for propeller-driven and jet aircraft• Identify the parameters to maximise range and endurance for propeller-driven
and jet aircraft• Describe the propulsion, aerodynamics and structural aspects in maximising
range and endurance
Session No. 2 Aircraft Steady and Level Flight – 2
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At the end of the session, the students will be able to :• Discuss the G-force and its types in relation to aircraft performance• Calculate the level turn performance of an aircraft• Explain the effect of load factor on aircraft turn performance• Calculate the pull-up and pull-down performance of an aircraft• Construct the V-n diagram and explain its importance in aircraft performance and
design
Session No. 3 Aircraft Accelerated Flight – 1
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Session No. 4 Aircraft Accelerated Flight – 2
At the end of the session, the students will be able to :• Differentiate take off and landing requirements of different types of aircraft• Calculate the take off performance of an aircraft• Explain balanced field length requirements for aircraft take off• Calculate the landing performance of an aircraft• Calculate the climb performance of an aircraft
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At the end of the session, the students will be able to :• Distinguish equilibrium and stability of an aircraft• Explain the six degrees of freedom of an aircraft in flight• Describe the conditions for static stability of an aircraft• Explain the necessity of trimming an aircraft for stability• Estimate the stability characteristics of an aircraft • Derive the relationship between neutral point and static margin
Session No. 5 Aircraft Equilibrium, Stability and Control
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Session No. 6Aircraft Longitudinal Static Stability
At the end of this session the students will be able to :• Classify the various aircraft control surfaces• Differentiate handling qualities of conventional and fly-by-wire aircraft• Categorise the forces and moments acting on an aircraft• Derive the conditions for longitudinal static stability of an aircraft• Estimate the hinge moment coefficient• Analyse the longitudinal static stability of an aircraft with canard
configuration• Analyse the longitudinal static stability of tailless aircraft
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Session 7Aircraft Lateral Static Stability
At the end of this session the students will be able to :• Differentiate two types of lateral motion of an aircraft• Derive the conditions for yaw stability of an aircraft• Estimate the hinge moment coefficient of rudder• Explain the requirements of rudder sizing• Derive the conditions for roll stability of an aircraft• Describe the effects of yaw-roll coupling• Explain directional stability of an aircraft
©M. S. Ramaiah University of Applied Sciences
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Session 8Aircraft Manoeuvrability
At the end of this session the students will be able to :• Define manoeuvrability of an aircraft• Explain the handling characteristics of an aircraft• Estimate control surface effectiveness• Estimate hinge moments• Estimate stick forces• Describe control reversal
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Session 9Aircraft Flight Dynamics – 1
At the end of this session the students will be able to :• Describe the axes and notation for the analysis of dynamic stability of an
aircraft• Derive the generalised set of equations of motion for a rigid aircraft• Construct the linearised form of equations of motion
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Session 10Aircraft Flight Dynamics – 2
At the end of this session the students will be able to :• Derive the three degree of freedom equations of motion for an aircraft• Construct the linearised form of equations of motion• Formulate the equations of motion in state space form
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Laboratory Sessions
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Session No. 1 Performance calculations using MATLAB
At the end of this session, students will be able to :• Calculate the thrust required of a jet aircraft using MATLAB • Calculate the thrust available in a jet aircraft using MATLAB
©M. S. Ramaiah University of Applied Sciences
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Session No. 2 Performance calculations using MATLAB
At the end of this session, students will be able to :• Calculate the power required of a propeller-driven aircraft using MATLAB • Calculate the power available in a propeller-driven aircraft using MATLAB
©M. S. Ramaiah University of Applied Sciences
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Session No. 3 Performance calculations using MATLAB
At the end of this session, students will be able to :• Calculate the turn performance characteristics of an aircraft using MATLAB
©M. S. Ramaiah University of Applied Sciences
31Faculty of Engineering & Technology
Session No. 4 Performance calculations using MATLAB
At the end of this session, students will be able to :• Calculate the pull-up and pull-down performance characteristics of an
aircraft using MATLAB• Calculate the climb performance characteristics of an aircraft using MATLAB
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Session No. 5 Performance calculations using MATLAB
At the end of this session, students will be able to :• Calculate the take off and landing performance characteristics of an aircraft
using MATLAB
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Session No. 6 Performance calculations using Piano-X
At the end of this session, students will be able to :• Evaluate the detailed performance characteristics of Fokker 70, a narrow
body, twin-engined, medium-range, turbofan aircraft using Piano-X
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Session No. 7 Performance calculations using Piano-X
At the end of this session, students will be able to :• Evaluate the detailed performance characteristics of Airbus A380, a double-
deck, wide-body and four-engined aircraft using Piano-X
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Session No. 8Static stability calculations using MATLAB
At the end of this session, students will be able to :• Estimate the longitudinal static stability characteristics of an aircraft using
MATLAB
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Session No. 9 Static stability calculations using MATLAB
At the end of this session, students will be able to :• Estimate the lateral static stability characteristics of an aircraft using MATLAB
©M. S. Ramaiah University of Applied Sciences
37Faculty of Engineering & Technology
Session No. 10 Dynamic stability calculations using MATLAB
At the end of this session, students will be able to :• Estimate the dynamic stability characteristics of an aircraft using MATLAB
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