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Aeronautical Engineering V SEM BOOKLET

EDITED BY

AERONAUTICAL ENGG.DEPTT.

NNSS SAMALKHA GROUP OF INSTITUTIONS

1

Academic Calendar (Session August – December 2014)

B. Tech. S. No. Details Date

1. Revision Exercise before 1st sessional Exams - 3rd – 4th October, 2014 (Thursday to Saturday)

2. 1st Sessional Exams (One and half Units) - 7th -10th October, 2014 (Tuesday to Friday)

3. 1st Sessonal Result - 15th October, 2014 (Wednesday)

4. Revision Exercise before 2nd sessional Exams - 7th to 8th November, 2014 (Thursday to Saturday)

5. 2nd Sessional Exams (Next one & half Units) - 10th – 13th November, 2014 (Monday to Thursday)

6. 2nd Sessonal Result - 18th November, 2014 (Tuesday)

7. 3rd Sessional (In class Room)(Full Syllabus) - 01st – 4th December, 2014 (Monday to Thursday)

M. Tech. (CSE, ECE, EEE, CE & ME) S. No. Details Date

1. 1st Sessional Examination - 17-18th October, 2014 (Friday-Saturday)

2. 2nd Sessional Examination - 28-29th November, 2014 (Friday-Saturday)

BBA & MBA S. No. Details Date

1. 1st Sessional Examination - 7th-14th October,2014 (Tuesday to Tuesday)

2. 2nd Sessional Examination - 10th – 17th November, 2014 (Monday to Monday)

Fresher’s Party Schedule

S. No. Department Venue Date 1. C. S. E. SH1/A2 Block 20th September, 2014 (Saturday)

2. E. C. E. & E. E. E. SH1/A2 Block 27th September, 2014 (Saturday)

3. M. B. A. and B. B. A. SH1/A2 Block 18th October, 2014 (Saturday)

4. M. E. & M.E. (Auto) SH1/A2 Block 15th November, 2014 (Saturday)

5. C. E. and Aero. Engg. SH1/A2 Block 22nd November, 2014 (Saturday)

List of Pending Holidays in Session 2014-15 (Odd Semester)

S. No. Name of Holiday Date Day of the week

1 Raksha Bandhan 10th August SUNDAY

2 Independence Day 15th August FRIDAY

3 Janmashtmi 18th August MONDAY

4 Mahatma Gandhi Birthday 2nd October THURSDAY

5 Dusshera 3rd October FRIDAY

6 Id-ul-Zuha(Bakrid) 6th October MONDAY

7 Diwali 23rd October THURSDAY

8 Vishwa Karma Day 24th October FRIDAY

9 Haryana Day 1st November SATURDAY

10 Guru Nanak Birthday 6th November THURSDAY

11 Christmas Day 25th December THURSDAY

2

TABLE OF CONTENT

Scheme of examination 3

Aerodynamics II syllabus 4

Aerodynamics II lecture plan 5-7

Aerodynamics II assignment 8-9

Aircraft Structures-II syllabus 10

Aircraft Structures-II lecture plan 11

Aircraft Structures-II assignment 12-19

Aircraft Materials and Manufacturing Processes

syllabus

20


lecture plan

21


assignment

22-23

Elements of Aeronautics syllabus 24

Elements of Aeronautics lecture plan 25-26

Elements of Aeronautics assignment 27-28

Microprocessor and Interfacing syllabus 29

Microprocessor and Interfacing lecture plan 30-32

Microprocessor and Interfacing assignment 33-36

Propulsion-I syllabus 37-38

Propulsion-I lecture plan 49-40

Propulsion-I assignment 41-44

Training Report Practical 45

Propulsion Lab 46

Cad Cam Lab 47

3

SCHEME OF EXAMINATION

B.TECH. 3rd

Year Aeronautical Engineering -5th

Semester

Course No.

Course Title

Teaching Schedule

Examination schedule

Total

Marks

Duratio

n of

Exam

L T P/D Total Theor

y

Sessio

nal

Practic

al

Viva

ARE-301E Aerodynamics II 3 1 - 4 100 50 - 150 3

ARE 303 E

Aircraft Structures-II 3 1 - 4 100 50 - 150 3

ARE-305E Aircraft Materials and

Manufacturing Processes

3 1 - 4 100 50 - 150 3

ARE-307E Elements of Aeronautics 3 1 - 4 100 50 - 150 3

ECE-311E Microprocessor and Interfacing 4 1 - 5 100 50 - 150 3

ARE-309E Propulsion-I 3 1 - 4 100 50 - 150 3

ARE-311 E Training Report Practical - - - - - 50 - 50 3

ARE-313 E Propulsion Lab - - 3 3 - 25 25 50 3

ARE-315E Cad Cam Lab - - 2 2 - 25 25 50 3

TOTAL 19 6 5 30 600 400 50 1050 -

4

B. Tech. (Fifth Semester) Aeronautical Engineering

Aerodynamics II

ARE-301E

Sessional : 50 Marks

L T P Theory : 100 Marks

3 1 - Total : 150 Marks

Duration of Exam. : 3 Hrs. NOTE: In the semester examination, the paper setter will set 8 questions in all, at least two questions from

each unit, and students will be required to attempt only 5 questions, selecting at least one from each unit.

UNIT-I

CONFORMAL TRANSFORMATION Complex potential function, Blasius theorem, principles of conformal transformation, Kutta -Juokowaski

transformation of a circle into flat plate, airfoils & ellipses.

INCOMPRESSIBLE FLOW OVER AIRFOILS

Glauert’s thin airfoil theory, symmetrical airfoil, cambered airfoil, flapped airfoil, determination of mean camber line

shapes for uniform & linear distribution of circulation. Description of flow about multi-element airfoils.

UNIT-II

INCOMPRESSIBLE FLOW OVER FINITE WINGS

Downwash & induced drag, Biot-Savart’s law and Helmholtz’s theorem, Prandtl’s classical lifting line theory,

fundamental equations. Elliptic and general lift distribution over finite unswept wings, effect of aspect ratio, Drag

polar ,Correlation of Cl distribution over other aspect ratios, Lifting Surface theory, Formation Flying, Ground effect.

UNIT-III

COMPUTATIONAL AERODYNAMICS OF AIRFOILS AND WINGS Computation of flow field due to distribution of source doublet and line and horse shoe vortices, vortex lattic

method,wing as a planar surface covered with HSVs.

UNIT-IV

DELTA WING AERODYNAMICS

Polhamus theory, leading edge suction analogy, calculations of lift coefficient, flow field, aspect ratio effect, leading

edge extension, HAA aerodynamics

Unit-VI COMPRESSIBLE SUBSONIC FLOWS OVER AIRFOILS The derivation of velocity potential equation. Linearization , Prandtl-Glauert compressibility correction. Karman –

Tsien correction, Critical Mach number, Whitcomb’s area rule, Super critical airfoil.

TEXT BOOKS: 1. Fundamentals of Aerodynamics : John D.Anderson,2nd Ed. McGrawHill,1991

2. Aerodynamics for Engineers : Bertin and Smith,Prentice Hall,1989

REFERENCES:

1 Aerodynamics for engineering students ; Houghten EL & Brock AE

5

Lesson Plan: Aerodynamics-II

Unit Topic Lecture No.

1

2

CONFORMAL TRANSFORMATION

Complex potential function

2

Blasius theorem 2

principles of conformal transformation 1

Kutta Juokowaski transformation of a circle into

flat plate 2

airfoils & ellipses.

INCOMPRESSIBLE FLOW OVER AIRFOILS

Glauert’s thin airfoil theory 1

symmetrical airfoil 1

cambered airfoil 1

flapped airfoil 1

determination of mean camber line shapes for

uniform & linear distribution of circulation 2

Description of flow about multi-element airfoils.

2

3

INCOMPRESSIBLE FLOW OVER FINITE

WINGS

Downwash & induced drag 1

Biot-Savart’s law and Helmholtz’s theorem 2

Prandtl’s classical lifting line theory, fundamental

equations 3

Elliptic and general lift distribution over finite

unswept wings 3

effect of aspect ratio, Drag polar

Correlation of Cl distribution over other aspect 2

6

ratios

Lifting Surface theory, Formation Flying 2

Ground effect 1

4

DELTA WING AERODYNAMICS

Polhamus theory 2

leading edge suction analogy 2

calculations of lift coefficient 1

flow field, aspect ratio effect 1

leading edge extension

1

HAA aerodynamics 2

5

COMPRESSIBLE SUBSONIC FLOWS OVER

AIRFOILS

The derivation of velocity potential equation 2

Linearization 1

Prandtl-Glauert compressibility correction 2

Karman –Tsien correction 2

Critical Mach number 1

Whitcomb’s area rule 2

Super critical airfoil 1

7

Assignment 1

1. Write down the Blasius theorem.

2. Describe the complex potential functions over an aerofoil.

3. Discuss the application of kutta Joukowski transformation.

4. Describe the Effect of spoiler.

5. What are the measures of thin aerofoil design?

6. Describe the Boot strap generator.

Assignment 2

1. Write short notes on: - symmetrical airfoil, cambered airfoil, flapped airfoil.

2. Describe the Glauert’s thin airfoil theory.

3. Determination of mean camber line shapes for uniform & linear distribution of circulation.

4. Description of flow about multi-element airfoils.

5. Write down downwash and upwash.

6. What is ground effect?

Assignment 3

1. Describe lifting line theory.

2. Discuss the formation of various flying.

3. Describe the Aspect Ratio.

4. Write down About Drag polar.

5. Discuss the distribution over infinite Swept wings.

6. Discuss the doublet flow.

Assignment 4

1. Write down about Horseshoe vortex.

2. Discuss about the planeform vortices lattice.

3. Write about creation of vortex.

4. Discuss about Vortex Generator.

5. State Polhamus theory.

6. Describe about the leading edge analogy.

Assignment 5

1. What is the Decalage?

2. State the Aerofoil Matrix.

3. What is functionless deficiency of camber Aerofoil?

4. State Navier-Strokes Equation.

5. Describe the Drag divergence.

6. State the Blasius theory.

8

Assignment 6

1. A hot-air balloon with an inflated diameter of 30 ft is carrying a weight of SOO Ib, which includes the weight of the hot air

inside the balloon. Calculate (a) its upward acceleration at sea level the instant the restraining ropes is released and (b) the

maximum altitude it can achieve. Assume that the variation of density in the standard atmosphere is given by p = 0.002377 (I -

7 x 10-6 h) 4.21, where h is the altitude in feet and p is in slug/ft3.

2. Consider the particular flow that exists for the case where e = 1.0 m, h = 0.01 m, V∞ = 240 m/s, and M∞ = 0.7. Also, consider

a fluid element of fixed mass moving along a streamline in the flow field. The fluid element passes through the point (x/e, y/n

= (~, I). At this point, calculate the time rate of change of the volume of the fluid element, per unit volume.

3. State Pressure differences over Curved body.

4. Describe the Delta Wing Characteristics.

5. Describe Mach Number.

6. Describe the differences between divergent and convergent.

Assignment 7

1. State Whitcomb Area rule.

2. What is Stagger?

3. Describe about Aerodynamic Balancing.

4. What is Critical Mach number?

5. Describe Super Critical Aerofoil?

6. Describe Wings tailoring?

Assignment 8

1. State Importance of momentum Equations in case compressible and invisid flows.

2. Plot Drag divergence graph as over 5 mach.

3. What is Uniform stagnation Flow?

4. Describe the laminar Flows.

5. How turbulent flow is reduced?

6. State NACA233112.

9

B. Tech. (Fifth Semester) Aeronautical Engineering Aircraft Structures-II

ARE 303 E L T P/D Total Sessional : 50 Marks

3 1 - 4

Theory : 100Marks

Total : 150 Marks

Duration of Exam: 03 hours

NOTE: In the semester examination, the paper setter will set 8 questions in all, at least two questions from


UNIT I UNSYMMETRICAL BENDING

Bending stresses in beams of unsymmetrical sections – Bending of symmetric sections with skew loads.

SHEAR FLOW IN OPEN SECTIONS Thin walled beams, Concept of shear flow, shear centre, Elastic axis. With one axis of symmetry, with wall effective and

ineffective in bending, unsymmetrical beam sections.

UNIT II

SHEAR FLOW IN CLOSED SECTIONS

Bredt – Batho formula, Single and multi – cell structures. Approximate methods. Shear flow in single & multicell

structures under torsion. Shear flow in single and multicell under bending with walls effective and ineffective.

UNIT III

BUCKLING OF PLATES

Rectangular sheets under compression, Local buckling stress of thin walled sections, Crippling stresses by Needham’s and

Gerard’s methods, Thin walled column strength. Sheet stiffener panels. Effective width, inter rivet and sheet wrinkling

failures.

UNIT IV

STRESS ANALYSIS IN WING AND FUSELAGE

Procedure – Shear and bending moment distribution for semi cantilever and other types of wings and fuselage, thin webbed

beam. With parallel and non parallel flanges, Shear resistant web beams, Tension field web beams (Wagner’s).

Text books: 1. Megson, T.M.G., “Aircraft Structures for Engineering Students”, Edward Arnold, 1995.

2. Perry, D.J., and Azar, J.J., “Aircraft Structures”, 2nd

edition, McGraw–Hill, N.Y., 1993.

Reference books

1. Rivello, R.M., “Theory and Analysis of Flight Structures”, McGraw-Hill, 1993

2. Bruhn. E.H. “Analysis and Design of Flight vehicles Structures”, Tri – state off set company, USA, 1985

10

LECTURE PLAN

Aircraft Structures-II

Unit

No.

Topic Lect.

No.

1

UNIT I UNSYMMETRICAL BENDING

Bending stresses in beams of unsymmetrical sections 2

– Bending of symmetric sections with skew loads. 2

SHEAR FLOW IN OPEN SECTIONS

Thin walled beams 2

Concept of shear flow 2

shear centre, Elastic axis 2

With one axis of symmetry, with wall effective and ineffective in bending,

unsymmetrical beam sections.

3

2

SHEAR FLOW IN CLOSED SECTIONS

Bredt – Batho formula 2

Single and multi – cell structures. Approximate methods 2

Shear flow in single & multicell structures under torsion 3

Shear flow in single and multicell under bending with walls effective and

ineffective 3

3

BUCKLING OF PLATES

2

Rectangular sheets under compression, Local buckling stress of thin walled

sections, 3

Crippling stresses by Needham’s and Gerard’s methods, Thin walled column

strength. 3

Sheet stiffener panels. Effective width, inter rivet and sheet wrinkling failures.

4

4

STRESS ANALYSIS IN WING AND FUSELAGE

Procedure – Shear and bending moment distribution for semi cantilever and other

types of wings and fuselage, thin webbed beam 4

With parallel and non parallel flanges 2

Shear resistant web beams, Tension field web beams (Wagner’s).

3

11

Assignment -1

1. State Bending Stress over unsymmetrical section.

2. Describe Shear Centre.

3. Discuss the concept of shear flow.

4. Describe Bredt – Batho formula.

5. Discuss the Multi cell Structure in Composite matrix.

Assignment 2

1. A beam 2400mm long is supported at two points A and B which are 144Omm apart; point A is

360mm- from the left-hand end of the beam and point B is 600 mm from the right-hand end;

the value of EZ for the beam is 240 x lo8 N mm2.

Find the slope at the supports due to a load of 2000N applied at the mid-point of AB. Use the reciprocal

theorem in conjunction with the above result, to find the deflection at the mid-point of AB due to loads of

3000N applied at each of the extreme ends of the beam.

2. A circular fuselage frame shown in Fig. P.4.19, of radius r and constant bending stiffness EI, has

a straight floor beam of length r ≈2, bending stiffness EI, rigidly fixed to the frame at either end.

The frame is loaded by a couple T applied at its lowest point and a constant equilibrating shear

flow q around its periphery. Determine the distribution of the bending moment in the frame,

illustrating your answer by means of a sketch. In the analysis, deformations due to shear and

end load may be considered negligible. The depth of the frame cross-section in comparison with the radius r may also be neglected.

1

Q q

EI

450 450

4

T

3

12

3. The frame is loaded in its own plane by a system of point loads P which are balanced by a constant shear flow

q around the outside. Determine the distribution of the bending moment in the frame and sketch the bending

moment diagram. In the analysis take bending deformations only into account.

4. Write about the Pure Bending Momentum over a thin plate.

5. A plate 10 mm thick is subjected to bending moments M, equal to 10 N m/mm and My equal to 5 N m/mm.

Calculate the maximum direct stresses in the plate.

6. The plate of the previous two problems is subjected to a twisting moment of 5 N m/mm along each edge, in addition

to the bending moments of M, = 10 N m/mm and My = 5 N m/mm. Determine the principal moments in the plate,

the planes on which they act and the corresponding principal stresses

13

ASSIGNMENT -3

1. A column of length 21 with the doubly symmetric cross-section shown in is compressed between the parallel platens

of a testing machine which fully prevents twisting and warping of the ends.Using the data given below, determine the

average compressive stress at which the column first buckles in torsion I = 500 mm; b = 25.0 mm, t = 2.5 mm, E = 70

000 N/mm2, EIG = 2.6

2. A simply supported beam has a span of 2.4m and carries a central concentrated load of 10 kN. The flanges of the

beam each have a cross-sectional area of 300mm2 while that of the vertical web stiffeners is 280mm'. If the depth of the beam, measured between the centroids of area of the flanges, is 350 mm and the stiffeners are symmetrically

arranged about the web and spaced at 300 mm intervals, determine the maximum axial load in a flange and the

compressive load in a stiffener. It may be assumed that the beam web, of thickness 1.5 mm, is capable of resisting

diagonal tension only.

3. What do you understand by an Airy stress function in two dimensions? A beam of length 1, with a thin rectangular

cross-section, is built-in at the end x = 0 and loaded at the tip by a vertical force P. Show that the stress distribution,

as

Calculated by simple beam theory, can be represented by the expressionq5 = Ay3 + By3x + C ~ X as an Airy

stress function and determine the coefficients A, B, C.

4. A metal plate has rectangular axes Ox, Oy marked on its surface. The point 0 and the direction of Ox are fixed in

space and the plate is subjected to the following uniform stresses: compressive, 3p, parallel to Ox, tensile, 2p,

parallel to Oy, shearing, 4p, in planes parallel to Ox and Oy in a sense tending to decrease the angle xOy Determine

the direction in which a certain point on the plate will be displaced; the coordinates of the point are (2, 3) before

straining. Poisson’s ratio is 0.25.

5. A solid shaft of circular cross-section supports a torque of 50 kNm and a bending moment of 25 kNm. If the

diameter of the shaft is 150 mm calculate the values of the principal stresses and their directions at a point on the

surface of the shaft.

6. A shear stress T, ~ac ts in a two-dimensional field in which the maximum allowable shear stress is denoted by T~~ and

the major principal stress by aI.Derive, using the geometry of Mohr's circle of stress, expressions for the maximum

values of direct stress which may be applied to the x and y planes in terms of the three parameters given above.

ASSIGNMENT -4

1. Discuss Prandtl Stress Function In Straight Bar with Uniform Section.

2. What is lines of Shear Stress or Shear Lines.

3. Show that the stress function 4 = k (r2 - a2) is applicable to the solution of a solid circular section

bar of radius a. Determine the stress distribution in the bar in terms of the applied torque, the rate

of twist and the warping of the cross-section’s it possible to use this stress function in the solution

for a circular bar of hollow section?

4. Deduce a suitable warping function for the circular section bar of P.3.1 and hence derive the

expressions for stress distribution and rate of twist.

5. Determine the maximum shear stress

and the rate of twist in terms of the applied torque T for the section comprising narrow rectangular

strips.

14

6. Describe Different Types of Riveted

and Bolted Joints used in Aircraft Structure.

ASSIGNMENT -5

1. Write Short Notes On: - Ailerons, Flaps, Rudder, and Elevator.

2. What is FOD?

3. Why Fail safe design is necessary to Aircraft Design? What is Safe-life.

4. Define Damage Tolerance Limits.

5. A panel, comprising flat sheet and uniformly spaced Z-section stringers, a part of whose cross-section is shown in

is to be investigated for strength under uniform compressive loads in a structure in which it is to be stabilized by

frames a distance 1 apart, 1 being appreciably greater than the spacing b. (a) State the modes of failure which you

would consider and how you would determine appropriate limiting stresses. (b) Describe a suitable test to verify

your calculations, giving particulars of the specimen, the manner of support, and the measurements you would

take. The latter should enable you to verify the assumptions made, as well as to obtain the load supported.

Ts C

YS

ds Area=AS

6. Part of a compression panel of internal construction is shown in Fig. P.6.17. the equivalent pin-centre length of the

panel is 500mm. The material has a Young’s modulus of 70 000 N/mm2 and its elasticity may be taken as falling

catastrophically when a compressive stress of 300 N/mm2 is reached. Taking coefficients of 3.62 for buckling of a

plate with simply supported sides and of 0.385 with one side simply supported and one free, determine (a) the load

per mm width of panel when initial buckling may be expected and (b) the load per mm for ultimate failure. Treat

the material as thin for calculating section constants and assume that after initial buckling the stress in the plate

increases parabolically from its critical value in the centre of sections.

3mm

30mm 3.5mm

120mm

16

ASSIGNMENT -6

1. State the Law of Equilibrium Of elasticity.

2. State the Mohr Circle of stress.

3. Discuss 2D problems with Inherent to Stress Function Polar Quadrants.

4. Discuss with mathematical Explanations of Inverse and Semi Inverse Functions.

5. A timber beam 16 cm wide and 20 cm deep is to be reinforced by steel strips each 16 cm

wide and 1 cm thick. Find the moment of resistance when (i) the steel strips are attached

at the top and bottom so that overall all depth is 22 cm and (ii) the steel strips are

attached symmetrically at the sides so that overall width is 18 cm. Allowable stress in the

timber is 6 mpa.

6. State the difference between Torsion and Torque.

ASSIGNMENT -7

1. Describe Compression Bending.

2. Define Maximum Stress Theory.

3. Describe the wing Constructions of Aircraft.

4. Why Rigging is required for A/C Structural Design.

5. Describe Shear.

6. A uniform, semi-circular fuselage frame is pin-jointed to a rigid portion of the structure and is

subjected to a given temperature distribution on the inside. The temperature falls linearly across

the section of the frame to zero on the outer surface. Find the values of the reactions at the pin-

joints and show that the distribution of the bending moment in the frame is

M =0.59EIaθo COS Ψ/ h

ASSIGNMENT -8

1. A beam 2400mm long is supported at two points A and B which are 144Omm apart; point A is

360mm- from the left-hand end of the beam and point B is 600 mm from the right-hand end; the

value of EZ for the beam is 240 x lo8 N mm2.

Find the slope at the supports due to a load of 2000N applied at the mid-point of AB. Use the reciprocal

theorem in conjunction with the above result, to find the deflection at the mid-point of AB due to loads of

3000N applied at each of the extreme ends of the beam.

2. A circular fuselage frame shown in Fig. P.4.19, of radius r and constant bending stiffness EI, has a

straight floor beam of length r ≈2, bending stiffness EI, rigidly fixed to the frame at either end. The

frame is loaded by a couple T applied at its lowest point and a constant equilibrating shear flow q

around its periphery. Determine the distribution of the bending moment in the frame, illustrating

your answer by means of a sketch. In the analysis, deformations due to shear and end load may be

considered negligible. The depth of the frame cross-section in comparison with the radius r may also be neglected.

17

1

Q q

EI

450 450

4

T

3

3. The frame is loaded in its own plane by a system of point loads P which are balanced by a constant shear flow q

around the outside. Determine the distribution of the bending moment in the frame and sketch the bending moment

diagram. In the analysis take bending deformations only into account.

4. Write about the Pure Bending Momentum over a thin plate.

5. A plate 10 mm thick is subjected to bending moments M, equal to 10 N m/mm and My equal to 5 N m/mm. Calculate the

maximum direct stresses in the plate.

6. The plate of the previous two problems is subjected to a twisting moment of 5 N m/mm along each edge, in addition to the

bending moments of M, = 10 N m/mm and My = 5 N m/mm. Determine the principal moments in the plate, the planes on

which they act and the corresponding principal stresses

18

B. Tech. (Fifth Semester) Aeronautical Engineering Aircraft Materials and Manufacturing Processes

ARE 305 E L T P/D Total Sessional : 50 Marks

3 1 - 4

Theory : 100 marks

Total : 150 Marks



each unit, and students will be required to attempt only 5 questions, selecting at least one from each unit. UNIT1

Introduction Properties of flight vehicle materials, Importance of strength/weight ratio of materials for Aerospace

Vehicles: Structures, Importance of temperature variations, factors affecting choice of material for different parts of

airplane.

Metallurgy Alloying Theory, Binary diagrams, iron-carbon diagram, Aluminum-copper diagram, structure- property correlation,

General Characteristics of Metallic Materials- Stress- strain curve, fatigue, creep, corrosion and prevention, Surface

hardening of metals, weld ability, formability & machineability.

UNIT 2

Aircraft Steels Classification of alloy steels, Effect of alloying elements, Carbon steels v/s Alloys steels, corrosion resistant steels, Heat

treatment, Corrosion prevention methods, Selection and application of steel alloys to aircraft manufacture

Light Metal Alloys Aluminum alloys, Heat treatment, High strength and high corrosion resistant alloys, Magnesium alloys and their properties,

Heat treatment. Application to Aerospace Vehicle of these alloys.

UNIT 3

High Strength and Heat Resistant Alloys Classification of heat resistant materials and iron, Nickel and cobalt base alloys, Refractory materials:Ceramics, Titanium

and its alloys, properties of Inconel, Monal and K-Monal, Nimonic and super alloys: Application to Aerospace

vehicles.Transparent Materials, plastic, Rubber,Synthetic Rubber wood, Fabrics. UNIT 4

COMPOSITE MATERIALS: Definition-Advantages and Disadvantages-Materials and its Compositions-Types of Moulding-HoneyComb Design –

Nomex-Curing Processes-Pre-peg-Vacuum Bagging.

Aircraft Manufacturing Processes Profiling, Hydro forming, mar forming bending rolls, Spar milling, Spark erosion and Powdered metal parts, integral

machining, Contour etching, High energy rate forming, Manufacturing of honeycomb structures, General methods of

construction of aircraft and aero engine parts.

Text Books: 1. G.F.Titterton, “Aircraft Materials and Processes”, Himalayan Books, New Delhi

2. Cindy Foreman-Advanced Composites-Jeppessen Ltd.

References 1. Chapman WAJ, “Workshop Technology”, Vol. I, II, III.

3. G.B.Ashmead, “Aircraft Production Methods”. :

4. Lalit Gupta, “Advanced Composite Matertials”, Himalayan Books, New Delhi, 1998

Note: Eight questions are to be set two questions from unit-1, 2 & 4 and one from unit-3 & 5. Students have two attempt

five questions.

19

unit Introduction Aircraft Materials and Manufacturing Processes

I

Properties of flight vehicle materials, Importance of strength/weight ratio of materials for

Aerospace

3

Vehicles: Structures, Importance of temperature variations, factors affecting choice of material for

different parts of airplane

3

Metallurgy Alloying Theory, Binary diagrams, iron-carbon diagram, Aluminum-copper diagram, structure-

property correlation

3

General Characteristics of Metallic Materials- Stress- strain curve, fatigue, creep, corrosion and

prevention, Surface hardening of metals, weld ability, formability & machineability.

4

II

Aircraft Steels

Classification of alloy steels, Effect of alloying elements, Carbon steels v/s Alloys steels, corrosion

resistant steels

2

Heat treatment, Corrosion prevention methods, Selection and application of steel alloys to aircraft

manufacture

3

Light Metal Alloys Aluminum alloys, Heat treatment, High strength and high corrosion resistant alloys

2

Magnesium alloys and their properties, 2

Heat treatment. Application to Aerospace Vehicle of these alloys 2

III

High Strength and Heat Resistant Alloys

Classification of heat resistant materials and iron 1

Nickel and cobalt base alloys, Refractory materials:Ceramics, Titanium and its alloys 2

properties of Inconel, Monal and K-Monal, Nimonic and super alloys 2

Application to Aerospace vehicles.Transparent Materials, plastic, Rubber,Synthetic Rubber wood,

Fabrics.

3

20

Assignment 1

1. Describe the construction of airplane.

2. What is core metallurgy?

3. Describe the critical point.

4. What is SAE?

5. Describe the steel compositions in aircraft part.

6. Write down the variation of flight vehicles.

.

Assignment 2

1. What is carbon matrix?

2. What is unit cell?

3. Describe BCC AND FCC

4. Describe the principle of lattice cell.

5. What are allotropy properties of carbon alloy?

6. Discuss the difference between Carbon Alloy and Steel Alloy.

Assignment 3

1. Describe the Stress –strain curve.

2. Discuss Aluminum-copper diagram.

3. What is prevention from corrosion?

4. Discuss the different type of Corrosion.

5. Describe the Characteristics of Metallic Steel.

6. Describe heat treatment process.

IV

COMPOSITE MATERIALS:

Definition-Advantages and Disadvantages-Materials and its Compositions- 1

Types of Moulding-HoneyComb Design –Nomex-Curing Processes-Pre-peg-Vacuum Bagging 2

Aircraft Manufacturing Processes Profiling, Hydro forming, mar forming bending rolls, Spar milling, Spark erosion and Powdered

metal parts

2

integral machining, Contour etching, High energy rate forming, Manufacturing of honeycomb

structures,

3

General methods of construction of aircraft and aero engine parts.

2

21

Assignment 4

1. Write Short notes on: - Annealing, Full Annealing and Spherodizing.

2. Define Normalizing.

3. Define Case Hardening.

4. What are Carburizing and its properties?

5. Define 18-8 SS.

6. What is Nitriding?

Assignment 5

1. Discuss the selection procedure of steel alloys for manufacturing Aircraft.

2. Discuss about alloy verification.

3. What is alodizing?

4. What is anodizing?

5. What is tempering?

6. What is bath procedure used in Nitride treatment?

Assignment 6

1. Write the application of Magnesium Alloy and its properties.

2. Describe the application Aerospace vehicles.

3. What is Nitro- Alloy?

4. Discuss about Nickel Alloy.

5. Describe the progressive use of Plastics polymer.

6. Discuss about thermoset and thermosetting.

Assignment 7

1. What is Composite Structure?

2. Write down the pros and cons of Composite Structure.

3. Define Reinforced Fiber.

4. What is Matrix Material?

5. Define Aramid.

6. What is the Application of pro and pre catalyst?

Assignment 8

1. Write down the Formation of Honeycomb Structure.

2. Write down about the Tempered Glass.

3. Write About Mongoose Structure.

4. Discuss the linear pattern of Semi Solid Formation.

5. What is Hydro forming?

6. Discuss Applications of Pre peg and Vacuum Bagging.

22

B. Tech. (Fifth Semester) Aeronautical Engineering Elements of Aeronautics ARE 307 E

L T P/D Total Sessional : 50 Marks

3 1 - 4

Theory : 100 marks

Total : 150 Marks



each unit, and students will be required to attempt only 5 questions, selecting at least one from each unit. UNIT-I

HISTORICAL AIRCRAFT DESIGN EVALUATION

Early airplanes, biplanes and monoplanes, Developments in aerodynamics, materials, structures and propulsion over the

years. Components of an airplane and their functions. Different types of flight vehicles, classifications. Conventional control,

Powered control, Basic instruments for flying, Typical systems for control actuation.

UNIT-II

INTRODUCTION TO PRINCIPLES OF FLIGHT

Physical properties and structure of the atmosphere, Temperature, pressure and altitude relationships, Evolution of lift, drag

and moment. Aerofoils, Mach number, Maneuvers.

UNIT-III

INTRODUCTION TO AIRPLANE STRUCTURES AND MATERIALS

General types of construction, Monocoque, semi-monocoque and geodesic construction, Typical wing and fuselage

structure. Metallic and non-metallic materials, Use of aluminum alloy, titanium, stainless steel and composite materials.

UNIT-IV

POWER PLANTS USED IN AIRPLANES

Basic ideas about piston, turboprop and jet engines, Use of propeller and jets for thrust production. Comparative merits,

Principles of operation of rocket, types of rockets and typical applications, Exploration into space.

Text Books:

1. Anderson, J.D., “Introduction to Flight”, McGraw-Hill, 1995.

REFERENCES:

1. Kermode, A.C., “Flight without Formulae”, McGraw-Hill, 1997.

23

LECTURE SCHEDULE FOR Elements of Aeronautics

S.No

TOPICS No. Of

Lectures

References

1 HISTORICAL AIRCRAFT DESIGN EVALUATION

Early airplanes, biplanes and monoplanes, Developments in aerodynamics, materials,

structures and propulsion over the years. Components of an airplane and their

functions. Different types of flight vehicles, classifications. Conventional control,

Powered control, Basic instruments for flying, Typical systems for control actuation

5

1,2

3,4

4,5

T1, T2

2 INTRODUCTION TO PRINCIPLES OF FLIGHT

Physical properties and structure of the atmosphere, Temperature, pressure and

altitude relationships, Evolution of lift, drag and moment. Aerofoils, Mach number, Maneuvers.

8

6,7

8,9

10,11

12,13

T1, T2

3 INTRODUCTION TO AIRPLANE STRUCTURES AND MATERIALS

General types of construction, Monocoque, semi-monocoque and geodesic

construction, Typical wing and fuselage structure. Metallic and non-metallic

materials, Use of aluminum alloy, titanium, stainless steel and composite

materials.

5

14,15

16

17,18

T1,

4 POWER PLANTS USED IN AIRPLANES

Basic ideas about piston, turboprop and jet engines, Use of propeller and jets for thrust

production. Comparative merits, Principles of operation of rocket, types of rockets and

typical applications, Exploration into space.

11

19,20

21,22

23

24,25

26,27

28,29

T1, T2

24

Consider the same flat plate under the same external flow conditions. Calculate the friction drag on the plate assuming a

turbulent boundary layer for a freestream velocity of (a) 100 m/s, and (b)

Assignment 1

1. What is Aerofoil?

2. What is up wash and down wash?

3. What is the nomenclature of Aerofoil?

4. What is Mean camber line?

5. What are the types of Airfoils?

6. What is Buffeting?

Assignment 2

1. What is Fluttering?

2. Discuss About the atmospheric conditions depend on the Aircraft.

3. Describe about the primary control Surfaces.

4. What are the applications of Auxiliary control Surfaces?

5. What are the uses of slats and slots?

6. What is Flap and describe its Types.

Assignment 3

1. Discuss application for new design aerofoil.

2. State Drag Conditions,

3. Describe Propulsion.

4. 1000 m/s.

5. What is Turbulence Modeling?

6. Consider Mach 4 flow at standard sea level conditions over a flat plate of chord 5 in. Assuming all laminar flow and adiabatic

wall conditions, calculate the skin friction drag on the plate per unit span.

Assignment 4

1. State Mach number.

2. What is Vortex Line over High cambered Aerofoil?

3. Discuss Horseshoe Vortex.

4. State Historical influence of Glider and justification over symmetrical Aerofoil.

5. Discuss Lifting Line Theory and Its limitations.

6. Describe Thin Aerofoil Theory.

25

Assignment 5

1. State the Newton Laws of Viscosity.

2. State uses of propeller.

3. Describe Boundary Layers.

4. Why Yaw causes Roll?

5. Define adverse yaw.

6. What are Decalage and Stagger?

Assignment 6

1. Define Mach number.

2. Describe Supersonic and Subsonic Flows.

3. What are Difference between Convergent and divergent Nozzles?

4. Discuss the types of Aerofoil.

5. State nomenclature of an Aerofoil.

6. What the purpose of Wind tunnel Testing.

Assignment 7

1. Discuss the type of Wind tunnels.

2. State the difference between Low speed wind tunnel and High speed wind tunnel.

3. State the Equation of Blasius over thin plates.

4. Plot Drag VS Lift with help of DC=3.5 AND LC=8.6.

5. Describe the four Forces acting on Aerofoil.

6. Define Reynolds number.

Assignment 8

1. State Importance of momentum Equations in case compressible and invisid flows.

2. Plot Drag divergence graph as over 5 mach.

3. What is Uniform stagnation Flow?

4. Describe the laminar Flows.

5. How turbulent flow is reduced?

6. State NACA233112.

26

B. Tech. (Fifth Semester) Aeronautical Engineering 1. Microprocessor and Interfacing ECE 311 E

L T P/D Total Sessional : 50 Marks

4 1 - 5

Theory : 100 marks

Total : 150 Marks


NOTE: In the semester examination, the paper setter will set 8 questions in all, at least two

questions from each unit, and students will be required to attempt only 5 questions, selecting at

least one from each unit.

UNIT-I INTRODUCTION : Evolution of microprocessors, technological trends in microprocessor development. The

Intel family tree. CISC Versus RISC. Applications of Microprocessors. 8086 CPU ARCHITECTURE : 8086

Block diagram; description of data registers, address registers; pointer and index registers, PSW, Queue, BIU and

EU. 8086 Pin diagram descriptions. Generating 8086 CLK and reset signals using 8284. WAIT state generation.

Microprocessor BUS types and buffering techniques, 8086 minimum mode and maximum mode CPU module.

UNIT-II 8086 INSTRUCTION SET : Instruction formats, addressing modes, Data transfer instructions, string

instructions, logical instructions, arithmetic instructions, transfer of control instructions; process control

instructions; Assembler directives. 8086 PROGRAMMING TECHNIQUES : Writing assembly Language

programs for logical processing, arithmetic processing, timing delays; loops, data conversions. Writing

procedures; Data tables, modular programming. Macros.

UNIT-III MAIN MEMORY SYSTEM DESIGN : Memory devices, 8086 CPU Read/Write timing diagrams in minimum

mode and maximum mode. Address decoding techniques. Interfacing SRAMS; ROMS/PROMS. Interfacing and

refreshing DRAMS. DRAM Controller – TMS4500.

UNIT-IV BASIC I/O INTERFACE : Parallel and Serial I/O Port design and address decoding. Memory mapped I/O Vs

Isolated I/O Intel’s 8255 and 8251- description and interfacing with 8086. ADCs and DACs, - types, operation

and interfacing with 8086. Interfacing Keyboards, alphanumeric displays, multiplexed displays, and high power

devices with 8086. INTERRRUPTS AND DMA : Interrupt driven I/O. 8086 Interrupt mechanism; interrupt

types and interrupt vector table. Intel’s 8259. DMA operation. Intel’s 8237. Microcomputer video displays.

Text Books: 1. D.V.Hall , Microprocessors and Interfacing , McGraw Hill 2nd ed.

2. J Uffenbeck , The 8086/8088 family , (PHI).

3. Liu,Gibson , Microcomputer Systems – The 8086/8088 family, (2nd Ed-PHI).

.

27

LECTURE PLAN

MP (ECE-311E)

Unit

No. Topic Name Book Name

Page

No. Lec No.

Unit 1

INTRODUCTION : Evolution of

microprocessors The Intel Microprocessors barry B.

Brey 02--017

1

technological trends in

microprocessor development. 2

The Intel family tree Micro Computer System: the INTEL

8086/8088 Family- Liu & Gibson 22 3

CISC Versus RISC Notes from Internet 4

Applications of Microprocessors. Micro Computer System: the INTEL

8086/8088 Family- Liu & Gibson 22 5

8086 CPU ARCHITECTURE : 8086

Block diagram

Advance Microprocessors and

peropherals- A K Ray & K M

Bhurchandi

03--06 6

description of data registers, address

registers; pointer and index registers,

PSW, Queue, BIU

and EU



Bhurchandi

02--08 7,8

8086 Pin diagram descriptions



Bhurchandi

8--14 9

Generating 8086 CLK and reset

signals using 8284.

The Intel Microprocessors barry B.

Brey

307-

322

10

WAIT state generation 11

Microprocessor BUS types and

buffering techniques 12

8086 minimum mode and maximum

mode CPU module



Bhurchandi

21--28 13,14

28

Unit 2

8086 INSTRUCTION SET :

Instruction formats, addressing modes



Bhurchandi

38--74 15,16

Assembler directives



Bhurchandi

74--82 17

8086 PROGRAMMING

TECHNIQUES : Writing assembly

Language programs for logical

processing



Bhurchandi

86--123 18

Writing procedures

Micro Computer System: the INTEL

8086/8088 Family- Liu & Gibson

155--

179

19

Data tables, modular programming.

Macros 20

Unit 3

MAIN MEMORY SYSTEM

DESIGN : Memory devices



Bhurchandi

157--

173 21

8086 CPU Read/Write timing

diagrams in minimum mode and

maximum mode



Bhurchandi

21--28 22,23

Address decoding techniques.

Interfacing SRAMS; ROMS/PROMS.

Interfacing and refreshing

DRAMS. DRAM Controller –

TMS4500



Bhurchandi

158--

173 24,25

Unit 4

BASIC I/O INTERFACE : Parallel

and Serial I/O Port design and address

decoding



Bhurchandi

173--

181 26,27

Memory mapped I/O Vs Isolated I/O

Intel’s 8255 and 8251-description and

interfacing with 8086



Bhurchandi

184--

200 28,29,30

ADCs and DACs, - types, operation

and interfacing with 8086



Bhurchandi

212--

228 31

Interfacing Keyboards, alphanumeric

displays, multiplexed displays, and

high power devices with 8086



Bhurchandi

181--

184 32,33

INTERRRUPTS AND DMA :

Interrupt driven I/O

Micro Computer System: the INTEL

8086/8088 Family- Liu & Gibson

240--

250 34

29

8086 Interrupt mechanism; interrupt

types and interrupt vector table.

Microprocessor and Interfacing- D V

Hall

8.1--

8.12 35

Intel’s 8259. Microprocessor and Interfacing- D V

Hall

8.30--

8.36 36

DMA operation. Intel’s 8237.



Bhurchandi

306-

318 37

Microcomputer video displays The Intel Microprocessors barry B.

Brey

517--

529 38

Suggested Books:

1. D.V.Hall , Microprocessors and

Interfacing , McGraw Hill 2nd ed.

2. J Uffenbeck , The 8086/8088

family , (PHI).

3. Liu,Gibson , Microcomputer

Systems – The 8086/8088 family,

(2nd Ed-PHI

30

MICROPROCESSORS & INTERFACING

(ECE-311E)

Assignment No. 1

1. Differentiate between RISC and CISC based Systems. What are two units makeup the 8086 processor?

Explain the functioning of BIU and EU? (BT-5/D11)

2. (a) Draw the functional block diagram and explain the features of clock generator 8284 used with 8086.

(b) What is the role of pointer and index registers in 8086? How they can be used, explain with the help

of examples. (BT-5/D09)

3. (a) Explain the technological trends in Microprocessor development.

(b) Explain the Intel family tree. (BT-5/D08)

4. (a) Explain in detail the execution unit of 8086 µP. What are the applications of registers present in EU?

(b) Discuss in brief that how the evolution of microprocessors took place. What are the various

applications of µPs. (BT-5/D05)

5. Write the historical steps of generation of microprocessors. (BT-5/DX)

6. Explain the following pins of 8086 microprocessor:

(BT-5/D7)


(ECE-311E)

Assignment No. 2

1. Explain at least 10 advantages of RISC and CISC Architecture. (BT-5/D07)

2. (a) Give the pin diagram of 8086 µP chip. Discuss the functions of each pin.

(b) Discuss how 8086 clock and reset signals are generated using 8284. (BT-5/D06)

3. (a) What is the function of 8086 queue and how does it speed up process operation?

(b) Explain the difference between 8086 working in minimum mode and maximum mode.

(BT-5/D05)

4. Explain the microprocessor bus types and buffering techniques. (BT-5/DX)

5. Explain the Block architecture of 8086. Draw and explain 8086 flag register format.

(BT-5/D11)

6. What is the role of pointer and index register in 8086? (BT-5/D09)


(ECE-311E)

Assignment No. 3

1. Explain the following instructions: SAR, POPF, XLAT, JNP/JPO and STD. (BT-5/D07)

2. What is the difference between recursive and recurrent procedure? Write the program for finding the

value of n factorial. (BT-5/D06)

3. (a) Explain the instruction format of 8086 µP.

(b) What do you understand by procedures and macros. (BT-5/D05)

31

4. What is the use of data transfer instruction? Explain the following instructions with suitable examples:

MOV, POP, LEA, AAA, LDS/LES. (BT-5/DX)

5. Write with the help of examples the difference between Branch and loop instructions of 8086

microprocessor. (BT-5/D11)

6. Explain the following pins of 8086: NMI, TEST, DEN, BHE, READY. (BT-5/D09)


(ECE-311E)

Assignment No. 4

1. Write a program to calculate to compute the factorial for a number N between 1 and 8.

(BT-5/D07)

2. Spot the grammatical syntax errors in the following:

a. MOV BH, AX

b. IN BL, 04H

c. ADD Al, 2073H (BT-5/D06)

3. (a) Write 8086 instruction that will perform the indicated operation.

i. Copies AL to BL

ii. Copies DL to a mem. Location whose offset is in BX.

(b) What do you understand by the term modular programming? (BT-5/D05)

4. Explain the following directives: ASSUME, ENDP, EXTRN, OFFSET EQU, ORG and SUM.

(BT-5/D11)

5. Describe the operation performed by following instructions:

a. MOV [SI],BX

b. AND BX,[SI]

c. AAA

d. IMUL CL

e. SBB BX, CX (BT-5/D09)

6. Write a delay loop which produces a delay of 500 µs on an 8086 with a 5 MHz clock.

(BT-5/D08)


(ECE-311E)

Assignment No. 5

1. What are advantages of DRAM over SRAM? Explain the concept of interfacing and refreshing of

DRAM with the help of a functional block diagram of DRAM. (BT-5/D08)

2. Draw and explain the timing waveform for read operation of 8086 in minimum mode.

(BT-5/D09)

3. List the advantages of Memory Segmentation. Discuss how segmentation is useful in 8086

microprocessor and also explain the memory segmentation in 8086. (BT-5/D11)

4. What are the various types of memory devices available and their advantages?

(BT-5/D07)

32

5. What do you understand by the term DRAM controller? Discuss the working of TMS-4500.

(BT-5/D06)

6. Describe the memory mapped I/O and direct I/O. Give the main advantages and disadvantages of each.

(BT-5/D05)


(ECE-311E)

Assignment No. 6

1. How address decoding is done in 8086 while interfacing ROM chips? Discuss with the help of some

examples. (BT-5/D05)

2. Draw and explain the timing diagram of 8086 during Read/Write operation. (BT-5/D06)

3. What is the function of an address decoder? Explain with the help of an example.

(BT-5/D07)

4. (a) Explain how the control bus signals are produced for an 8086 system operating in maximum mode.

(b) Explain why DMA data transfer faster than doing the same data transfer with program instructions.

(BT-5/D11)

5. Design and interface between 8086 cpu and two chips of 16K*8 EPROM and two chips of 32K*8 RAM.

Select the starting address of EPROM in F8000H and the RAM address must start at 00000H.

(BT-5/DX)

6. Write a short note on “Microcomputer video displays”. (BT-5/D12)


(ECE-311E)

Assignment No. 7

1. Define an interrupt. Describe the interrupt response of 8086 (BT-5/D04)

2. Explain the operation, characteristics, specifications, applications and interfacing of D/A converter

with 8086 (BT-5/D08)

3. Why you cannot connect the I/O devices directly to a system bus? Explain.

(BT-5/DX)

4. Sketch and explain the interfacing of PPI 8255 to the 8086 microprocessor in minimum mode.

(BT-5/D09)

5. Explain the internal clock diagram and initializing steps of and intel 8259 priority interrupt controller.

(BT-5/D11)

6. Draw the block diagram of 8251 and explain the function of each block. (BT-5/D07)


(ECE-311E)

Assignment No. 8

1. What is 8259 chip? Discuss its use and operation in a 8086 microprocessor based system.

(BT-5/D07)

2. Write notes on microcomputer video display. (BT-5/D06)

33

3. Discuss briefly the D/A converter operation and application respect to interfacing with µP.

(BT-5/D05)

4. Describe the interrupt vector table and interface 8*8 keyboard. (BT-5/D09)

5. Write notes on Alphanumeric displays. (BT-5/D11)

6. What do you understand by Direct Memory Access? Draw the diagram to interface DMA with µP.

(BT-5/DX)

34

B. Tech. (Fifth Semester) Aeronautical Engineering Propulsion-I

ARE 309E L T P/D Total Sessional : 50 Marks

3 1 - 4

Theory : 100 Marks

Total :150 Marks




UNIT-I

FUNDAMENTALS OF GAS TURBINE ENGINES

Illustration of working of gas turbine engine – The thrust equation – Factors affecting thrust – Effect of pressure, velocity and

temperature changes of air entering compressor – Methods of thrust augmentation – Characteristics of turboprop, turbofan and turbojet

– Performance characteristics.

SUBSONIC AND SUPERSONIC INLETS FOR JET ENGINES

Internal flow and Stall in subsonic inlets – Boundary layer separation – Major features of external flow near a subsonic inlet – Relation

between minimum area ratio and eternal deceleration ratio – Diffuser performance – Supersonic inlets – Starting problem on supersonic

inlets – Shock swallowing by area variation – External declaration – Models of inlet operation.

UNIT-II

COMPRESSORS

Principle of operation of centrifugal compressor – Work done and pressure rise – Velocity diagrams – Diffuser vane design

considerations – Concept of prewhirl – Rotation stall – Elementary theory of axial flow compressor – Velocity triangles – degree of

reaction – Three dimensional – Air angle distributions for free vortex and constant reaction designs – Compressor blade design –

Centrifugal and Axial compressor performance characteristics.

UNIT-III

COMBUSTION CHAMBERS

Classification of combustion chambers – Important factors affecting combustion chamber design – Combustion process – Combustion

chamber performance – Effect of operating variables on performance – Flame tube cooling – Flame stabilization – Use of flame holders

– Numerical problems.

UNIT-IV

NOZZLES

Theory of flow in isentropic nozzles – Convergent nozzles and nozzle choking – Nozzle throat conditions – Nozzle efficiency – Losses

in nozzles – Over expanded and under – expanded nozzles – Ejector and variable area nozzles – Interaction of nozzle flow with

adjacent surfaces – Thrust reversal

35

PROPELLERS

Types-uses-Aerodynamics forces acting,, selection of propellers, fixed, variable and constant speed pro pellers, prop-fan, material for

propellers, shrouded propellers helicopter ,rotor in hovering performance.

.

Text Books:

1. Cohen, H. Rogers, G.F.C. and Saravanamuttoo, H.I.H. “Gas Turbine Theory”, Longman, 1989.

2. Oates, G.C., “Aero thermodynamics of Aircraft Engine Components”, AIAA Education Series, New York, 1985.

3. “Rolls Royce Jet Engine” – Third Edition – 1983.

4. Mathur, M.L. and Sharma, R.P., “Gas Turbine, Jet and Rocket Propulsion”, Standard Publishers & Distributors, Delhi, 1999.

36

LECTURE PLAN

PROPULSION-I (ARE-309E)

unit topic days

FUNDAMENTALS OF GAS TURBINE ENGINES

Illustration of working of gas turbine engine – The thrust equation – Factors

affecting thrust 2

– Effect of pressure, velocity and temperature changes of air entering

compressor – Methods of thrust augmentation 3

Characteristics of turboprop, turbofan and turbojet – Performance

characteristics.

2

–SUBSONIC AND SUPERSONIC INLETS FOR JET ENGINES

Internal flow and Stall in subsonic inlets – Boundary layer separation – Major

features of external flow near a subsonic inlet

3

– Relation between minimum area ratio and eternal deceleration ratio – Diffuser

performance – Supersonic inlets 3

– Starting problem on supersonic inlets – Shock swallowing by area variation –

External declaration – Models of inlet operation.

4

COMPRESSORS

2 Principle of operation of centrifugal compressor – Work done and pressure rise 2

– Velocity diagrams – Diffuser vane design considerations – Concept of

prewhirl – Rotation stall – Elementary theory of axial flow compressor 3

– Velocity triangles – degree of reaction – Three dimensional – Air angle

distributions for free vortex and constant reaction designs

3

Compressor blade design – Centrifugal and Axial compressor performance

characteristics.

2

COMBUSTION CHAMBERS

3 Classification of combustion chambers – 1

Combustion chamber performance – 2

Effect of operating variables on performance 1

37

Important factors affecting combustion chamber design – Combustion process 2

–– Flame tube cooling – Flame stabilization – Use of flame holders – Numerical

problems.

3

NOZZLES

4 Theory of flow in isentropic nozzles – Convergent nozzles and nozzle choking – 2

Nozzle throat conditions 1

– Nozzle efficiency – Losses in nozzles 2

– Over expanded and under – expanded nozzles 1

Ejector and variable area nozzles 1

–– Interaction of nozzle flow with adjacent surfaces 2

– Thrust reversal

1

38

ASSIGNMENT-1

1. Illustrate the working of gas turbine engine. 2. Draw simple diagram of gas turbine engine. 3. Write the thrust equation.

4. Factors affecting thrust describe.

5. Effect of pressure, velocity and temperature changes of air entering compressor .

6. Methods of thrust augmentation

7. Characteristics of turboprop, turbofan and turbojet.

8. Performance characteristics of turboprop, turbofan and turbojet.

ASSIGNMENT-2

1. What is supersonic and subsonic?

2. What is Boundary layer separation?

3. Major features of external flow near a subsonic inlet

4. Define relation between minimum area ratio and eternal deceleration ratio.

5. What is Shock swallowing by area variation?

6. External declaration – Models of inlet operation

ASSIGNMENT-3

1. Define Velocity diagrams – Diffuser vane design considerations .

2. Concept of prewhirl – Rotation stall

3. Elementary theory of axial flow compressor explains it.

4. Dimensional – Air angle distributions for free vortex and constant reaction designs

5. Centrifugal and Axial compressor performance characteristics

6. What is velocity triangles and degree of reaction?

39

ASSIGNMENT-4

.

1. Classification of combustion chambers.

2. Theory of flow in isentropic nozzles.

3. Convergent nozzles and nozzle choking.

4. Nozzle throat condition.

5. Define nozzle efficiency and what are losses in nozzles?

6. Over expanded and under – expanded nozzles.

ASSIGNMENT-5

1. Important factors affecting combustion chamber design

2. Combustion process – Combustion chamber performance

3. What is Flame tube cooling?

4. Flame stabilization

5. What is the use of flame holders?

6. Why combustion is required in engine?

40

ASSIGNMENT-6

1. What is the function of nozzle?

2. Ejector and variable area nozzles explain them.

3. Interaction of nozzle flow with adjacent surfaces

4. Thrust reversal defines it properly. 5. What are propellers?

6. Types-uses-Aerodynamics forces acting on propellers.

ASSIGNMENT-7

.

1 How we select propellers?

2. fixed, variable and constant speed pro pellers

3. What are material for propellers required.

4. What is rotor inhovering performance

5. What is pitch in propellers.

6. how propellers works in airplane flying.

41

ASSIGNMENT-8

1. What is shrouded propellers helicopter?

2. What are shock waves?

3. What is the importance of shock waves?

4. Define boundary layer and write formula.

5. Types of nozzles.

6. Define aspect ratio.

42

B. Tech. (Fifth Semester) Aeronautical Engineering Practical Training Report

ARE 309 E P/D Total Sessional : 50 marks

- - Duration of Exams. : 03 hours Student will submit summer training (about 8 weeks’ industrial training) report for his/her assessment.

43

B. Tech. (Fifth Semester) Aeronautical Engineering Propulsion Lab

ARE- 313E

L T P Sessional: 25 Marks

0 0 3 Practical: 25 Marks

Total: 50 Marks

Duration of Exam: 3 Hrs

List of Experiments:

1. Study the constructional details of axial flow compressor

2. Study the constructional details of centrifugal compressor

3. Study of accessory gear box and its construction

4. Study the constructional details of main fuel pump

5. Study the constructional details of combustion chamber

6. Study the constructional details of after burning system

7. Study the constructional details of piston engines

8. Study the functioning of complete jet engine

9. Study the constructional details of propellers

Note: At least Eight Experiments should be performed. Out of that Two Experiments may be performed

or designed and set by the concerned institute as per the scope of the syllabus.

44

B. Tech. (Fifth semester) Aeronautical Engineering Cad Cam Lab

ARE 315 E

L T P/D Total Sessional: 25 Marks

- - 2 2 Practical: 25 marks


List of Experiments

LIST OF EXPERIMENTS

1. Scaling, rotation, translation, editing, dimensioning – Typical CAD command structure. 2. Wire frame modeling – surface modeling 3. Solid Modeling 4. Taper Turning – Straight Interpolation 5. Taper Turning – Circular Interpolation 6. Incremental programme G 90 operation. 7. Mirroring. 8. Incremental Programme G 91 operation 9. Absolute Programme G 90 operation

10. Absolute Programme G 91 operation.

Note: At least Eight Experiments should be performed. Out of that Two Experiments may be performed

or designed and set by the concerned institute as per the scope of the syllabus.

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