course coverage summary and question bank … banks/ae/ii ane ii sem q.bank 2016... · course...

DEPARTMENT OF AERONAUTICAL ENGINEERING

COURSE COVERAGE SUMMARY

AND

QUESTION BANK

FOR

II B.TECH II SEMESTER

(2014 – 15)

MALLA REDDY COLLEGE OF ENGINEERING & TECHNOLOGY (Sponsored by CMR Educational Society)

(Affiliated to JNTU, Hyderabad, Approved by AICTE - Accredited by NBA & NAAC – ‘A’ Grade - ISO 9001:2008 Certified)

Maisammaguda, Dhulapally (Post Via Hakimpet), Secunderabad – 500100

INDEX

S.NO NAME OF THE SUBJECT

1 AERODYNAMICS - I

2 AIRCRAFT PRODUCTION TECHNOLOGY

3 ELECTRONICS & ELECTRICAL ENGINEERING

4 AEROSPACE VEHICLE STRUCTURES - I

5 INTROCUCTION TO SPACE TECHNOLOGY

6 FLIGHT MECHANICS - I

COURSE COVERAGE SUMMARY S.NO NAME OF THE

SUBJECT UNIT NO. NAME OF THE TEXT BOOK CHAPTERS COVERED

1 AD- I I Anderson, Bertin (1 & 2) and (1&2)(Ber)

II Anderson, Bertin 3, (and), & 4 (and), 4 (Ber)

III Bertin, Anderson 4(Ber), 15,17,18 (Ander)

IV Anderson 5

V Clancy 17

2 APT I P.C Sherma & P.N. Rao 1 & 2 from P.N Rao

II P.N. Rao & Raghuvamshi 3 & 4th

from Raghuvanshi5th & 6th

from P.N. Rao

III P.C Sherma 9th

chapter from P.C. Sherma

IV P.C Sherma 2nd

from P.C. Sherma

V P.C Sherma & O.P Khanna O.P. KHANNA

3 EEE I P.S Subramanyam

S.N Singh

Types of elements, ohms law resisive,inductive,capacitive networks Kirchhoff’s laws series ,parallel circuits star to delta and delta to star basic principle of indicating instruments PMMC MI instruments

II

P.S Subramanyam T.K.Nagasarkar and M.S.Sukhhija

principle of operation of generator emf equation types of DC motors, Torque equation three point starter

III

S.N Singh T.K.Nagasarkar and M.S.Sukhhija

principle of operation of transformer emf equation losses, efficiency, regulation alternator principle synchronous imdedance method slip torque characteristics applications

IV

K.Lal kishor S.Salivahanan

p-n junction diode V-I characteristics diode applications PNP and NPN transistor transistor as amplifier SCR characteristics and applications

V

K.Lal kishor J.B Gupta

principles of CRT Deflection , sensitivity electrostatic and magnetic deflection applications of CRO

4 AVS - I I Aircraft Structures for Engineering Students-T H G

Megson

Chapter 1

II Structural Analysis-A Unified Approach: D S Prakash Rao

Chapter 1,5

III T H G Megson Chapter 2

IV T H G Megson Chapter 8

V T H G Megson Chapter 4,5

5 FM – I I Martin E.E & Helley Chapter 1,2,3

II Martin E.E & Helley Chapter 4

III Martin E.E & Helley Chapter 5,7

IV Martin E.E & Helley Chapter 6

V Martin E.E & Helley Chapter 8,9,10

6 IST I SUTTON Chapter 5(Wiese/William)

II ANDERSON Chapter 8

III CORNELISSE

IV Wiesel / William Chapter 5(Wiesel/William)

V

1

R13 II – I B.TECH AERONAUTICAL ENGG

II B.TECH II SEMESTER – AERONAUTICAL ENGINEERING

AERODYNAMICS – I (R13)

MODEL PAPER – I

MAXIMUM MARKS: 75

PART A Marks: 25

i. All questions in this section are compulsory

ii. Answer in TWO to FOUR sentences.

1. State the applications of Aerodynamics.

2. Differentiate among Continuum and Free molecular flow.

3. Define aerodynamic heating. Give the expression for aerodynamic heating rate at the wall.

4. State the assumptions made in the thin airfoil theory. Give the fundamental equation of thin

airfoil theory. What is the aim of thin airfoil theory?

5. Define adverse pressure gradient. What are the effects of flow separation?

6. Define laminar boundary layer, critical Reynolds number, and turbulent boundary layer.

7. Define Vortex filament and state Helmholtz vortex theorem.

8. Define induced drag and drag polar

9. Define the terms critical mach number and drag divergence Mach number

10. Define advance ratio, axial velocity in relation with a propeller.

PART B Marks: 50

i. Answer only one question among the two questions in choice.

ii. Each question answer (irrespective of the bits) carries 10M.

11. Derive the energy equation by applying the fundamental principle to a suitable flow model.

OR

12. Using neat sketches, explain the flow behavior past stream lined bodies placed in different Mach

number regimes.

13. a. Define boundary condition. Explain infinity boundary condition and wall – boundary

condition.

b. Explain Rankine – oval. Derive the equation of Rankine – oval.

OR

14. A stationary circular cylinder is placed in a uniform flow stream of velocity V∞. Obtain the

equation of stream line pattern around the cylinder. Also sketch the pressure distribution over

the surface of the cylinder.

2


15. Define using neat sketch the viscous drag over a body placed in a uniform free stream. Explain

the concept of flow separation and the factors effecting it

OR

16. Obtain the laminar boundary layer thickness and skin friction drag for an incompressible flow

over a flat plate at zero angle of attack. (BLASIUS EQUATION)

17. a. Derive the fundamental equation of Prandtl’s lifting line theory.

b. Obtain the expressions for coefficients of lift, induced drag, effective angle of attack for an

elliptical wing plan-form. Explain the symbols used clearly.

OR

18. Define vortex filament and vortex sheet. Obtain the solution for lifting – flows over 2 – D

bodies using vortex panel method. State the advantages of panel method over thin airfoil theory.

19. Using a neat sketch, explain how lift is augmented by using

a. Flap systems

b. Circulation control wing

OR

20. Explain how the performance parameters of propulsive systems are obtained using Rankine –

Froude momentum theory. Derive the necessary equations. State all the symbols used clearly.

3




MODEL PAPER – II

MAXIMUM MARKS: 75

PART A Max Marks: 25



1. State Buckingham’s pi theorem. What is its significance?

2. Using neat sketches define the aerodynamic forces acting on an airfoil.

3. Define velocity potential and stream function. Obtain the governing equation for inviscid,

incompressible flow in terms of velocity potential and stream function.

4. Define the terms aerodynamic center and center of pressure.

5. Define the terms pressure drag, skin friction drag, parasite drag and profile drag.

6. State the significance of N- S equations.

7. Define wash – in and wash – out conditions.

8. Define the terms aerodynamic twist, downwash and effective angle of attack.

9. State any three lift augmentation and drag reduction techniques used in aircraft designs.

10. Define the terms thrust coefficient and coefficient of thrust.

PART B Marks: 50



11. a. Derive Momentum equation in integral form and differential form by applying the physical

principle to a suitable flow model. (10 M)

OR

12. Derive the Navier – stokes equation.

13. A circular cylinder spinning about its own axis is placed in a uniform free – stream of velocity

V∞. Obtain the expression for the lift generated over the cylinder. State all the symbols used

clearly.

OR

14. Consider lifting flow over a circular cylinder. The lift coefficient is given by 5. Calculate the

peak pressure coefficient, location of stagnation points and the points on the cylinder where the

pressure equals free stream static pressure.

4


15. Define pressure drag. Explain using neat sketches flow separation and the factors effecting flow

separation, and separation control.

OR

16. Define momentum thickness of a boundary layer and derive Von – Karman momentum integral

equation.

17. Using neat sketches, explain the effect of the presence of down wash on the local airfoil section.

How the characteristics of a finite wing are different when compared to the characteristics of

airfoil sections?

OR

18. Citing necessary examples, explain the effect the aspect ratio of wings on the performance

parameters.

19. Using neat sketches explain the use of winglets in drag control.

OR

20. Define air screw. Express the performance parameters of a propeller in non – dimensional

coefficients.

5




MODEL PAPER – III

MAXIMUM MARKS: 75




1. Define Reynolds number and Mach number. State their significance.

2. What are constant – property flows? State any three applications of constant – property flows.

3. State Kelvin’s circulation theorem.

4. For a thin symmetrical airfoil at an angle of attack of 20, calculate the coefficient of lift anf

coefficient of moment at the leading edge.

5. What are the approximations made while solving the incompressible flow over a flat plate

using Blasius equation?

6. Sketch the velocity profile and flow separation over an airfoil in a moving fluid. (fig 15.2 page

794, J. D. Anderson)

7. Give the fundamental equation for Prandtl’s lifting line theory.

8. Define elliptical loading.

9. Name the primary effects of using a slot (wing gap) on the boundary layer.

10. Define efficiency of a propeller.

PART B Marks: 50



11. Using Buckingham’s pi theorem, explain the factors on which the basic parameters of

aerodynamics depend on.

OR

12. a. Explain the criterion to be established for the flows to be dynamically similar.

b. Consider an aircraft cruising at a velocity of 245.87m/s at standard altitude of 11582.4 m,

where the free stream pressure and temperature are 20712.9 N/m2 and 216.67 K, respectively. A

one – fifth model of the craft is tested in a wind tunnel where the temperature is 238.88 K.

Calculate the required pressure and velocity of the test air stream in the wind tunnel such that

the aerodynamic coefficients measured for the wind tunnel model are same as for free flight.

Assume μ and a are proportional to T1/2

.

13. a. State Kutta condition.

6


b. Derive the fundamental equation of thin airfoil theory. Explain the symbols used clearly.

OR

14. a. Define source flow and sink flow. Obtain the expression for velocity potential and stream

function for the source flow. Define the strength of the source.

b. Consider a thin flat plate at 50, angle of attack. Using the results of thin airfoil theory,

calculate the lift coefficient, moment coefficient about the leading edge, moment coefficient

about the quarter chord point and the moment coefficient about the trailing edge.

15. a. Using neat sketch, explain the growth of a boundary layer over a flat plate. Define the terms

laminar boundary layer, turbulent boundary layer and transition boundary layer.

b. Define boundary layer thickness, energy thickness and momentum thickness.

OR

16. Example problems 18.1 and 19.1 of chapters 18 and 19 of J. D. Anderson

17. Consider a rectangular wing with an aspect ration of 6, an induced drag factor is given by 0.055

and a zero – lift angle of attack of -20. At an AoA of 3.4

0, the induced drag coefficient for this

wing is 0.01. Calculate the induced drag coefficient for a similar wing (a rectangular wing with

the same airfoil section) at the same angle of attack, but with an aspect ration of 10. Assume that

the induced factors for the drag and lift slope are equal to each other.

OR

18. .Explain the concept of vortex trunk and vortex theory by Lanchester.

19. Explain using necessary illustrations, how swept back wings are advantageous in reducing

transonic drag rise.

OR

20. Using neat sketches, explain the geometry of a propeller.

7




MODEL PAPER – IV

MAXIMUM MARKS: 75




1. Using a neat sketch, define transonic flow regime and explain fish tail pattern.

2. State the criterion for two or more flows to be dynamically similar.

3. Give the expression for pressure distribution on the surface of circular cylinder placed in a non

– lifting flow. Graphically represent it.

4. Define uniform flow, vortex flow and source flow.

5. What is the effect of surface roughness on transition point distance from the leading edge?

6. What is meant by a transport phenomenon? Define viscosity and thermal conduction.

7. What are the factors on which the lift and induced drag coefficients depend on?

8. State the significance of elliptical wing plan-form.

9. Define advance ratio, pitch and solidity of a propeller.

10. Briefly write about laminar flow control.

PART B Marks: 50



11. a. What are the sources of aerodynamic forces and moments? Explain using a neat sketch.

b. Explain the role of lift and drag coefficients in the preliminary design of an aircraft using neat

sketches. (REFER Pg. 45 DESIGN BOX of J. D. Anderson)

OR

12. a. Derive the continuity equation in integral form and differential form by applying the

fundamental principle to the suitable flow model.

b. State the significance of Reynolds number in aerodynamics.

13. From the fundamental equation of thin airfoil theory, obtain the aerodynamic force and moment

coefficients and the position of center of pressure for a cambered airfoil. Explain all the symbols

used clearly.

OR

8


14. Consider a non – lifting flow and lifting flow (of constant circulation) over the circular cylinder

of a given radius. For the two cases mentioned, if the free stream velocity is doubled, does the

shape of the stream lines change? Explain using necessary equations.

15. a. Define Viscosity.

b. Explain the role of viscosity in fluid flow and aerodynamics.

c. Define adverse pressure gradient

OR

16. Derive Navier – Stokes equations.

17. Define discretisation. State the importance of quarter – chord point and three – quarter chord

point in discretisation.

OR

18. Derive the fundamental equation of Prandtl’s lifting line theory. Apply it to solve for the

aerodynamic parameters of a rectangular swept back wing.

19. Define stall. Explain the effect of wing – section, wing plan – form and protuberances on the

performance of an aircraft.

OR

20. How does the air screw performance vary with the pitch of the blade? Explain.

9




MODEL PAPER – V

MAXIMUM MARKS: 75




1. Define with an example, surface forces and body forces acting on an object in fluid flow.

2. Using neat sketches show the various fluid flow models used for analyzing the flow.

3. Define the terms circulation, vorticity and turbulent flows.

4. State Kutta – Joukowski theorem. Brief the importance of friction in generating lift.

5. Give the expressions for energy thickness and momentum thickness of the laminar boundary

layer over a flat plate placed at zero angle of attack in a free stream of velocity V∞.

6. Using a neat sketch show the boundary layer properties. (Fig. 17.3 Pg. 870, J.D. Anderson)

7. Using a neat sketch show geometric, effective and induced angles of attack.

8. Define wing tip vortices, horse – shoe vortex and induced drag.

9. State the assumptions made in Rankine – Froude momentum theory of propulsion.

10. What are the factors on which the performance of a blade element depends on?

PART B Marks: 50



11. Explain how drag on a two – dimensional body is measured by applying momentum equation.

(refer Pg. 127 Section 2.6 of J. D. Anderson)

OR

12. Explain the importance of aerodynamics and applications of the subject in various fields of

engineering.

13. a. The lift on a spinning cylinder in a free stream with a velocity of 30 m/s and at standard sea

level conditions is 6 N/m of span. Calculate the circulation round the cylinder.

b. Consider a uniform flow of velocity V∞. Show that it is a possible case of incompressible

flow that is irrotational.

OR

14. State the fundamental equation of thin airfoil theory. Obtain the solution for the non – lifting

case using singularity distribution method.

10


15. Sketch the variation of variation of viscous drag coefficient with the Reynolds number over a

circular cylinder and explain.

OR

16. Define critical Reynolds number. State the effect of transition and surface roughness of airfoils

on its performance characteristics.

17. State the advantages and disadvantages of vortex panel method over thin airfoil theory while

solving for the performance parameters of an airfoil in incompressible inviscid flow.

OR

18. Consider a finite wing with an aspect ratio of 6. Assume an elliptical lift distribution. The lift

slope for the airfoil section is 0.1/degree. Calculate and compare the lift slopes for (a) straight

wing and a (b) swept wing with half – chord sweep of 450

19. a. Using neat sketches, explain how drag is reduced by using variable – twist and variable –

camber wings.

b. Explain power – augmented lift.

OR

20. Using blade – element theory, derive the equations necessary for predicting the performance of

the propulsive system. Explain all the symbols used clearly.

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY, HYDERABAD

II B. Tech II Semester Examination

AIRCRAFT PRODUCTION TECHNOLOGY

MODEL PAPER-I Time: 3 hours Marks: 75

Note: This question paper contains two parts A and B

Part A is Compulsory which carries 25 marks .Answer all questions in Part A. Part B consists of 5 Units.

Answer any one full question from each unit. Each question carries 10 marks and may have a,b,c, as sub

PART-A

1) Write the basic steps in the casting process.

2) Write the advantages of casting process.

3) Explain about single pint cutting tool nomenclature

4) Explain about single point drill bit cutting tool nomenclature

5) Compare the similarities and differences of ECM and EDM

6) Explain why EBM process is preformed usually in vacuum chamber

7) List the alloying materials of aluminum

8) Explain the principle of heat treatment

9) How many types of riveted joints? What are they?

10) What are the advantages in NDT

PART-B

11 A) Explain the principle of Arc welding with neat sketches.

B) Explain the principle of Electronic Beam welding with neat sketch.

(OR)

12. A)Explain the principle of Resistance welding and also explain resistance spot welding.

B) Explain about gas welding in details with neat sketch.

13. A) Explain about lathe machine in detail with neat sketch B) Explain about quick return mechanism in shaper machine

(OR) 14. A) Explain about radial milling machine with neat sketch

B) Explain about drilling machine with neat sketch

15. A) Explain the method of AJM with the help of a schematic diagram B) Explain about USM in detail with the help of neat sketch

(OR)

16. Explain why the mechanical properties of work piece materials are not significant in most of The NTMM 17. A) Discuss the alloying elements which improves strength of pure titanium

B) Discuss the application of titanium and its alloys (OR)

18. A) Discuss the process of anodizing of aluminum alloys B) Discuss the corrosion preventing methods of steel

19. A) Explain 3-2-1 Location principle with neat figures. B) Explain different mechanical clamping system used in fixtures

(OR)

20. A) How is metal inspected by ultrasonic testing and x-rays B) What are the advantages and drawbacks of ultrasonic machining process




MODEL PAPER-II Time: 3 hours Marks: 75




PART A

1) Discuss: Expandable mold casting, permanent molding casting and semi–permanent mold

casting.

2) Write the advantages and limitations of metal as the pattern material

3) Discuss the various pattern allowances.

4) Explain about up down milling process

5) Write about punching operation

6) Explain why the mechanical properties of work piece materials are not significant in most of

the NTMM

7) What is the effect of EDM on mechanical properties of work materials

8) Write short notes on harden ability of steel

9) How many types of riveted joints? What are they?

10) What are the advantages in NDT

PART.B

11. A) Explain the soldering and brazing techniques B) Explain the shell molding in detail with neat sketch

(OR)

12. A) Explain about die-casing in detail with neat sketch B) Explain in detail about Centrifugal casting with neat sketch.

13. Describe “Metal Spinning” write its product applications, differentiate between cold and hot Metal spinning.

(OR) 14. A) Explain the roll and importance of CNC machine in the field of aircraft industry

B) Explain the distinct features of CNC machines.

15) Explain about EDM in detail with the help of neat sketch (OR)

16) Explain about EBM & PAM in detail with the help of neat sketch 17) A) Explain how various alloys can be classified

B) Explain how aluminum alloys classified when used for aircraft application (OR)

18). Explain the initial stresses and the stress alleviation procedures in manufacturing

19) A) how is metal inspected by ultrasonic testing and x-rays B) What are the advantages and drawbacks of ultrasonic machining process?

(OR) 20) Explain the various types of rivets that are used in an aircraft industry justify your answer with Respect to the loads and atmospheric affects over an aircraft.




MODEL PAPER-III Time: 3 hours Marks: 75




PART-A

1) Write short notes on quenching.

2) What is jigs and fixture

3) What is the effect of EDM on mechanical properties of work materials

4) Explain the principle of LBM and PAM

5) Write about blanking operation

6) Give the advantages of sheet metal working process

7) Define the “deep drawing process”

8) Write about the following types of sands: facing sand, backing sand, system sand, and parting

sand.

9) What are the limitations of pressure die casting method?

10) Write the advantages and drawbacks of the “Welding Process”

PART-B

11). Explain in detail about Centrifugal casting with neat sketch. (OR)

12).A) Explain about Investment casting in detail with neat sketch B). Explain about shell mold casting in detail with neat sketch

13). what are the various methods of bending, describe each with neat sketch

(OR) 14) Compare “Metal spinning” with deep drawing

15) Explain about ECM in detail with the help of neat sketch

(OR) 16) List the principle advantages of

A) Arc welding over gas welding B) Gas welding over arc welding

17) A) why the cleaning of a joint is important before welding? B) Explain about welding techniques

(OR) 18) A) Explain sand properties?

B) Explain about sand casting in detail 19) Explain the tooling docks/tooling bars method in jig alignments

(OR) 20). what are advantages of using jigs and fixture in aircraft manufacturing


II B.Tech I Semester Examination

ELECTRICAL AND ELECTRONICS ENGINEERING


Note: This question paper contains two parts A and B.



Questions

PART-A

1) Answer all the Questions Marks: 25

a) State and explain Ohm’s law. 2M

b) What is meant by energy storing elements? Name them 3M

c) Why transformer rating in KVA. 2M

d) What is mean by regulation in transformer. 3M

e) Define Deflection torque and controlling torque. 2M

f) Write down the advantages of PMMC. 3M

g) Write down applications of diode. 2M

h) Define form factor and peak factor. 3M

i) Write down applications of CRO. 2M

j) What are the different measurements by using CRO. 3M

PART-B

2)

a) With a neat diagram explain the working principle of permanent magnet moving coil

instrument.

b) Write the advantages and disadvantages of PMMC instruments.

OR

3) Determine the current in the unbalanced bridge circuit shown in Figure 1. Find the value and

direction of current through the galvanometer. Neglect the internal resistance of the battery.

R13

4)

a) Derive the Torque equation of DC Motor b) Explain the basic principle of operation of D.C Motor

OR

5) A 25kW,250v dc shunt generator has armature and field resistance of 0.06Ω and 100Ω

respectively.Determine the total armature power developed and efficiency when working

a) As a generator delivering 25kW output and

b) as a motor taking 25kW input.

6)

a) Explain the working principle of a single phase transformer with a phasor diagram.

b) Define voltage regulation and efficiency of a transformer.

c) The full load copper and iron losses of a 15KVA, 1Ø, transformer are 320W and200W

respectively. Calculate the efficiency on

i) full load

ii) half load

When load power factor is 0.8 lagging in each case.

OR

7) Explain how regulation of an alternator can be estimated by synchronous impedance method

8) Explain the principle of operation of half wave bridge rectifier and draw the wave forms.

OR

9) Draw the basic band structure of NPN and PNP transistors and explain its operation.

10) Derive the expression for magnetic deflection sensitivity of a Cathode ray tube.

OR

11) With the help of block diagram explain the working principle of a CRT.








Questions

PART-A


a) Define resistivity. 2M

b) Derive an expression for the capacitance of a parallel circuit. 3M

c) Draw the Phasor diagram for the ideal transformer. 2M

d) Define Slip and Slip speed. 3M

e) What are the different types of instruments? 2M

f) What are the different types of dampings? 3M

g) Define TUF. 2M

h) Applications of SCR. 3M

i) Applications of CRO. 2M

j) What is the function of pre and post accelerating anodes? 3M

PART-B

2)

a) A 10Ω resistor is in series with a parallel combination of two resistors 15Ω and 5Ω. If the

current in the 5Ω resistor is 6A, what is the total power dissipated in the three resistors?

b) b)State and explain Kirchhoff’s laws

OR

3)

a) What are the different types of electrical measuring instruments?

b) Explain about different types controlling torques.

4)

a) Explain the basic principle of D.C generator.

b) A 6 pole wave wound D.C generator is having 50 slots with 25 conductors per slot and

rotating at 1500 rpm.The flux per pole is 0.015 Wb, calculate the emf generated.

OR

5)

a) Write the similarities and dissimilarities between the motor and generator.

b) The power input to a 230v dc shunt motor is 8477kw.The field resistance is 230Ωand

armature resistance is 0.28Ω find input current, armature current and back emf.

R13

6)

A 3phase 6 pole, 50 Hz cage motor is running with a slip of 4%. Find,

a) Speed of rotating field relative to stator winding.

b) Motor speed.

c) Slip speed.

d) Frequency of the emf induced in the rotor.

e) Speed of rotation of rotor mmf relative to rotor winding.

f) Speed of rotor mmf relative to stator winding

OR

7)

a) Explain the principle of operation and derive the emf equation of transformer.

b) A single phase 2300/230 V, 50 Hz core type transformer has core section of 0.05 m2. If

the permissible maximum Flux density is 1.1wb/m2, calculate the number of turns on

primary & secondary sides

8) Draw V-I characteristics of p-n diode and justify your answer with the help of a neat circuit

diagram explain the working principle of Single phase full wave rectifier.What is ripple

factor and obtain the ripple factor for single phase full wave rectifier.

OR

9)

a) Mention any four applications of PNP transistors.

b) Explain the principle of operation of SCR.

10) Derive the expression for magnetic deflection sensitivity of a Cathode ray tube.

OR

11) Name different components of CRT and write the function of each component.







Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c, as sub

Questions

PART-A


a) What are dependent sources? 2M

b) Define conductance and derive the expression. 3M

c) What are the different losses in transformer? 2M

d) Draw the slip-torque characteristics of induction motor. 3M

e) Define damping torque. 2M

f) Write the advantages and disadvantages of PMMC instruments. 3M

g) What is p-n junction and write its applications. 2M

h) Draw the V-I characteristics of SCR and justify your answer. 3M

i) How to measure voltage and frequency with CRO. 2M

j) Draw the block diagram of CRO. 3M

PART-B

2) Discuss the different types of torques required in an indicating instruments

OR

3)

a) Three resistances are connected in star, determine its equivalent delta configuration.

b) Derive the relation for conversion from delta to star connection.

4)

a) Explain back emf in DC motor

b) A 4 pole lap wound dc machine has 628 armature conductors. The flus per pole is 0.04wb.the

total armature current is 110A.find the torque developed

OR 5)

a) A long shunt compound generator delivers a load current of 5A at 500V and has

armature,series, field and shunt field resistance of 0.05Ω, 0.03Ω and 250Ω

respectively.Calculate the generated voltage and the armature current .allow 1v per brush for

contact drop.

b) Explain the OC characteristics of DC generator.

R13

6) A single phase 10 KVA, 2000/200 V, 50Hz transformer has impedance drop of 10% and

resistance drop of 5 %. Find the voltage regulation:

a) At full load at 0.8 power factor lagging.

b) At half the F.L at 0.6 Pf leading

c) An ideal 25kVA transformer has 500turns on the primary winding and 40 turns on the

secondary winding. The primary is connected to a 3000V, 50Hz supply. Calculate

i) Primary and secondary currents on full load

ii) Secondary emf

iii) The maximum core flux.

OR

7)

a) Explain the construction and working principle of three phase alternator.

b) Draw the slip-torque characteristics of a 3-phase Induction motor and justify your answer

with the suitable formulae.

8)

a) Explain the operation of a full wave bridge rectifier.

b) A single phase 230V, 1 kW heater is connected across single-phase 230V, 50Hzsupply

through a diode. Calculate the power delivered to the heater element

OR

9)

a) Discuss the characteristics of P-N junction diode

b) Explain the transistor as an amplifier

10) Explain the working of CRT with a block diagram

OR

11) Discuss voltage, current and frequency measurement using CRO.


II B.Tech I Semester Examination, Nov 2014


MODEL PAPER-IV Time: 3 hours Marks: 75


Part A is Compulsory which carries 25 marks .Answer all questions in Part A. Part B consists of 5

Units. Answer any one full question from each unit. Each question carries 10 marks and may have

a, b, c, as sub Questions

PART-A


a) State ohm’s law. What are its limitations? 2M

b) What is the function of commutator and brushes in d.c machines 3M

c) Define slip and rotor frequency 2M

d) What do you mean by transformation ratio? Write its significance 3M

e) Define controlling torque 2M

f) Advantages of moving iron 3M

g) What is ripple factor and PIV 2M

h) Mention any four applications of PNP transistors 3M

i) Give four applications of 2M

j) Write the principle of operation of CRT 3M

PART-B

2)

a) Explain the construction details and working principle of attraction type moving iron

instruments with the help of neat diagram.

b) Explain the eddy current damping with neat diagram.

OR 3)

a) Find the equivalent resistance across AB in the circuit shown below. All the resistances

are equal to 5Ω.

b) For the circuit shown in the fig find the total current and the magnitude of the impedance.

R13

4) With a neat sketch explain the purpose of 3-point starter used in dc motor.

OR

5)

a) Describe with the suitable sketches the main parts of a DC machine.Explain the main

functions of each part making specific reference to the properties of the material used for

the construction of each part.

b) A 250v short shunt compound generator is delivering 80 A.the armature series andshunt

field resistance are 0.05Ω and 0.03Ω respectively calculate the voltage induced allowing

a brush drop of 2v.

6) Explain the working principle of a 3 phase induction motor

OR

7)

a) Define voltage regulation and efficiency of a transformer.

b) A single phase 2200/250 V, 50 Hz transformer has a net core area of 36 sq.cm and a

maximum flux density of 6 Wb/m2. Calculate the number of turns of primary and

secondary windings.

8)

a) Explain the principle of operation of SCR

b) Explain how a transistor is used as an amplifier

OR

9) Explain the working principle of full bridge rectifier and obtain the formula for its ripple factor

10) Write the principle of operation of CRT

OR

11) Derive the expression for electrostatic deflection sensitivity of a Cathode ray tube


II B.Tech I Semester Examination, Nov 2014


MODEL PAPER-V Time: 3 hours Marks: 75


Part A is Compulsory which carries 25 marks .Answer all questions in Part A. Part B consists of 5

Units. Answer any one full question from each unit. Each question carries 10 marks and may have

a, b, c, as sub Questions

PART-A


a) What is meant by electrical conductance? What are its units? 2M

b) Explain the effect of temperature on resistance? 3M

c) What is the condition for maximum regulation in transformer 2M

d) Write the applications of 3-phase induction motor 3M

e) What are the different types of instruments 2M

f) Give some applications of M.I and M.C instruments? 3M

g) Draw V_I characteristics of p-n diode 2M

h) Define latching current and holding current 3M

i) What is mean by CRO 2M

j) Applications of CRO 3M

PART-B

2) Find V1 and V2 in the circuit shown in the fig

Explain KCL ,KVL and ohms law

OR

3) Discuss the different types of torques required in an indicating instruments 4)

a) Give the applications of dc compound motors.

b) A four pole 220v dc shunt motor has 540 lap wound conductors.it takes 32A from the

supply mains and develops power of 5.59kw.the field winding takes 1A. The armature

resistance is 0.9Ω and the flux per pole is 30 mwb calculate the speed and torque

developed

R13

OR

5) A 4 pole long shunt lap wound generator supplies 25 kw at a terminal voltage of 500v. The

armature resistance is 0.03Ω, series field resistance is 0.04Ω and shunt field resistance is

200Ω. The brush dropis taken as 1v determine

a) the emf generated

b) cu losses and iron losses

c) efficiency at full load

6)

a) Explain different types of losses in a transformer and write their significance in deciding

the rating of a transformer.

b) A 25 KVA,2200/220v 50Hz single phase transformer has the following resistance and

leakage reactance R1=0.8Ω,X1=3.2Ω,R2=0.01Ω, X2=0.03Ω calculate the equivalent

resistance and reactance refered to secondary side.

OR

7)

a) Explain the working principle of a Alternator

b) Explain the working principle of a 3 phase induction motor

8) Draw the basic band structure of SCR and explain its operation

OR

9) Explain the principle of operation of half wave bridge rectifier and draw the wave forms

10) Explain the application of CRO in the field of electrical measurements.

OR

11) Discuss how voltage, current and frequency are measured with CRO


II B.Tech. II Semester Examination

AEROSPACE VEHICLE STRUCTURES – I

MODEL PAPER – I

Time: 3 Hours Marks: 75


Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5

Units. Answer any one full question from each unit. Each question carries 10 marks and may

have a, b, c as sub.

PART – A

1. Describe the following briefly: (a) Plane Stress and (b) Plane Strain

2. Write down: (a) Three Longitudinal (or) Direct Strain Equations

(b) Three Shear Strain Equations

(c) Six Strain Compatibility Equations

3. Describe the following briefly: (a) Determinate Structures and (b) Redundant Structures

4. Explain: (a) Theorem-1 of Area-Moment Method

(b) Theorem-2 of Area-Moment Method

5. Describe the following briefly:

(a) Beams on Elastic Foundation and

(b) Modeling Concepts of Beams with Elastic Supports

6. Write down: (a) Equilibrium Equation for Curved Beam

(b) Deflection Equation of Curved Beam

7. Describe the following briefly: (a) Structural Stability and (b) Structural In-Stability

8. Show that Euler Buckling Load of Column:

9. Describe the following briefly: (a) Strain Energy and (b) Complementary Energy

10. Prove that

2

22

l

EInPCR

ydP

dC

dP

dU

Pdy

dC

dy

dU

PART – B

(OR)

(OR)

1. The simply supported rectangular beam shown in Figure 1 is subjected to two

symmetrically placed transverse loads each of magnitude Q . A rectangular

strain gauge rosette located at a point P on the centroidal axis on one vertical

face of the beam gave strain readings as follows: 610222 a , 610213 b

and 61045 c . The longitudinal stress x at the point P due to an external

compressive force is 2

7mm

N. Calculate the shear stress at the point P in the

vertical plane and hence the transverse load Q .

(Hint:3

2 bdQ where b = breadth, d = depth of beam)

Figure 1: Simply supported rectangular beam with strain gauge rosette

2. Direct stresses of 2

160mm

N(tension) and

2120

mm

N(compression) are applied at a

particular point in an elastic material on two mutually perpendicular planes.

The principal stress in the material is limited to 2

200mm

N(tension).

(a) Calculate the allowable value of shear stress at the point on the given planes.

(b) Determine also the value of the other principal stress and the maximum

value of shear stress at the point.

(c) Verify your answer using Mohr’s circle.

(OR)

(OR)

4. A non-uniform, single-span beam ABCD is simply-supported at A and D and

carries loading as shown in Figure 3. Determine the vertical displacement at B

using Area-Moment Method.

3. The beam is divided into two segments as shown in Figure 2.

(a) Determine the deflection and slopes at point B using Area-Moment Method.

(b) Draw shear force, bending moment diagrams and deflected curve.

(Given: 4610200,200 mmIGPaE )

Figure 2: Beam with two segments

Figure 3: Non-uniform, single-span beam ABCD

(OR)

(OR)

6. Derive beam deflection equation for discrete elastic supports using singularity

method.

7. A pin-ended column of length m0.1 has the cross-section shown in Figure 4. If

the ends of the column are free to warp determine the lowest value of axial load

which will cause the column to buckle, and specify the mode. Take

270000

mm

NE and

225000

mm

NG .

8. A uniform column of length L and flexural stiffness EI is simply supported at

its end sand has an additional elastic support at mid span as shown in Figure

5. This support is such that if a lateral displacement cv occurs at this point a

restoring force ckv is generated at the point. Derive an equation giving the

buckling load of the column. If the buckling load is 2

24

L

EI find the value of k .

Also if the elastic support is infinitely stiff show that the buckling load is given

by the equation 2/)2/tan( LL where EIP / .

Figure 5: Column

Figure 4: Column

5. Derive the direct solution of beam on elastic foundation.

(OR)

9. (a) Describe Bredt–Batho theory and derive Bredt–Batho formula.

(b) A thin-walled circular section beam has a diameter of mm200 and is m2

long; it is firmly restrained against rotation at each end. A concentrated torque

of kNm30 is applied to the beam at its mid-span point. If the maximum shear

stress in the beam is limited to 2/200 mmN and the maximum angle of twist to 02 , calculate the minimum thickness of beam walls. Take 2/25000 mmNG .

10. A steel rod of uniform circular cross-section is bent as shown in Figure 6, AB and

BC being horizontal and CD vertical. The arms AB, BC and CD are of equal length.

The rod is encastré at A and the other end D is free. A uniformly distributed load

covers the length BC. Find the components of the displacement of the free end D

in terms of EI and GJ.

Figure 6: Deflection of bent rod




MODEL PAPER – II






PART – A

1. Show that

2. Prove that

3. Describe the following briefly: (a) D.O.R. and (b) D.O.F.

4. Explain clearly: How can you bring a Redundant Structure into Determinate Structure ?




6. Write down: (a) Equilibrium Equation for Curved Beam with k1=0.0


7. Describe the following briefly: (a) Long Column (b) Medium Column and (b) Short Column

8. Explain Rankine and Jhonson’s Formulae.

9. Describe the following briefly: (a) Virtual Displacement and (b) Virtual Force

10. Write down the steps involved in Rayleigh-Ritz Method.

.

PART – B

(OR)

1. A cantilever beam of solid, circular cross-section supports a compressive load

of kN50 applied to its free end at a point mm5.1 below a horizontal diameter in

the verticalplane of symmetry together with a torque of Nm1200 as shown in

Figure 1. Calculate the directand shear stresses on a plane inclined at 060 to

the axis of the cantilever at a point onthe lower edge of the vertical plane of

symmetry.

Figure 1: Cantilever beam

2. A composite bar of length L has a central core of copper loosely inserted in a

sleeve ofsteel; the ends of the steel and copper are attached to each other by

rigid plates. If thebar is subjected to a temperature rise T determine the stress

in the steel and in thecopper and the extension of the composite bar. The copper

core has a Young’s modulus CE , a cross-sectional area CA and a coefficient of

linear expansion C ; the corresponding values for the steel are SE , SA and S .

(OR)

(OR)

3. Using the moment-area method, determine the slope at B and C and deflection

at C of the cantilever beam as shown in Figure 2. The beam is subjected to

uniformly distributed load over entire length and point load at the free end.

4. Determine the slope and deflection at the hinge of the beam shown in the Figure

3 using the moment-area method.

Figure 2: Cantilever Beam

Figure 3: Beam

(OR)

(OR)

5. Derive the direct solution of beam on elastic foundation.

7. Determine buckling load for a pin-ended column as shown in Figure 4.

Figure 4: Pin-ended column

8. Determine buckling load for a pin-ended perfect column as shown in Figure 5.

6. Derive beam deflection equation for discrete elastic supports using

singularity method.

Figure 5: Pin-ended column

(OR)

9. Calculate the vertical deflection of the point B and the horizontal movement of D

in the pin-jointed framework shown in Figure 6.

10. Determine the forces in the members of the truss shown in Figure 7 using

unit load method; the cross-sectional area A and Young’s modulus E are the

same for all members.

Figure 6: Pin-jointed framework

Figure 7: Truss




MODEL PAPER – III






PART – A

1. How Plane Stress condition is important in Aeronautical Engineering ?

2. Show that

3. Describe the following briefly: (a) Redundant Analysis Principles

4. Explain Singularity Method for Uniform Beams.




6. Write down: (a) Equilibrium Equation for Curved Beam with k1=0.0, k2=0.0


7. Describe the following briefly: (a) Eigen Values and (b) Eigen Modes

8. Write down: (a) Mode Shapes

(b) Critical Loads

9. Describe the following briefly: (a) Maxwell’s Reciprocal Theorem

10. Derive Bredt-Batho Formula when beam subjected to Torsion.

PART – B

(OR)

1. A cylindrical pressure vessel has an internal diameter of m2 and is fabricated

from plates mm20 thick. If the pressure inside the vessel is 2

5.1mm

Nand, in

addition, the vessel is subjected to an axial tensile load of kN2500 , calculate

the direct and shear stresses on a plane inclined at an angle of 060 to the axis

of the vessel. Calculate also the maximum shear stress.

(Hint: Use Figure 1 notation)

2. At a particular point in a structural member a two-dimensional stress system

exists where 2

60mm

Nx ,

240

mm

Ny and

250

mm

Nxy . If Young’s modulus

2200000

mm

NE and Poisson’s ratio 3.0 , calculate the direct strain in the x

and y directions and the shear strain at the point. Also calculate the principal

strains at the point and their inclination to the plane on which x acts; verify

these answers using a graphical method.

Figure 1: Stresses on a 2-D element

(OR)

(OR)

3. Determine the slope and deflection at B and C using area-moment method.

Figure 2: Non-uniform cantilever beam

4. Determine the end slope and deflection of the mid-point C in the beam shown

below (Figure 3) using moment-area method.

Figure 3: Simply supported beam

(OR)

(OR)

5. Derive the direct solution of a curved beam on elastic foundation.

208

015

853

)(

400

043

032

)( ba

6. Derive beam deflection equation for discrete elastic supports using

singularity method. Justify the derivation.

7. Find Eigen Values and Eigen Vectors of following Matrices:

8. The pin-jointed column shown in Figure 4 carries a compressive load P

applied eccentrically at a distance e from the axis of the column. Determine

the maximum bending moment in the column.

Figure 4: Eccentrically loaded column

(OR)

9. The thin-walled box section beam ABCD shown in Figure 5 is attached at each

end to supports which allow rotation of the ends of the beam in the longitudinal

vertical plane of symmetry but prevent rotation of the ends in vertical planes

perpendicular to the longitudinal axis of the beam. The beam is subjected to a

uniform torque loading of 20Nm/mm over the portion BC of its span. Calculate

the maximum shear stress in the cross-section of the beam and the distribution

of angle of twist along its length, G=70000N/mm2.

Figure 5: Thin-walled box beam

10. A uniform, thin-walled, cantilever beam of closed rectangular cross-section

has the dimensions shown in Figure 6. The shear modulus G of the top and

bottom covers of the beam is 18000N/mm2 while that of the vertical webs is

26000N/mm2.

(a) The beam is subjected to a uniformly distributed torque of 20Nm/mm along

its length. Calculate the maximum shear stress according to the Bredt–Batho

theory of torsion. Calculate also, and sketch, the distribution of twist along

the length of the cantilever assuming that axial constraint effects are

negligible.

Figure 6: Cantilever beam



INTRODUCTION TO SPACE TECHNOLOGY





PART-A

1) Discuss about the Different types of Altitudes?

2) What do you about the Space environment?

3) Explain About the A) Ballistic entry and B) Atmospheric entry?

4) Explain about the Skip entry and glide entry?

5) Write short notes on the Hohmann transfer?

6) Explain about the Bielliptical transfer?

7) Explain about the YO-YO mechanism?

8) What do you know about Attitude determination?

9) Discuss about the Ground system architecture?

PART-B

11 Derive the Rocket equation for the Multi stage Rocket with necessary diagrams?

(OR)

12 A) Explain in detail about the liquid and solid propellants

B) Explore about the Space Mission types

(OR) 13 A) . Derive the general equation of motion of for atmospheric entry?

(OR)

14. Discuss about the space vehicle trajectories with some basic aspects?

15. Derive the general equation of motion for two body motion? .

4. (OR)

16. Prove that the earth takes two days more than half a year to travel over half of its orbit separated by

Minor axis away from the sun. It is given that period of the earth is 365 days and the eccentricity of The orbit is 1/60 17. Derive the Equation of torque for the Axi-Symmetric body

(OR)

18. Discuss about Gradient satellite –Dual spin Spacecraft with the mathematical equations?

19. Discuss in detail about the following with appropriate sketches? A) Team responsibilities B) Mission Delivery

(OR)

20. Explain in detail about Spherical Geometry, Various Axes Systems with neat sketches?








PART A

1) Discuss about the Grain designs with figures?

2) Write about the Gravity turn Trajectories?

3) Explain about the Lifting Entry?

4) Write about the Aerodynamic heating?

5) Explain about the Gravity Loss with respect altitude?

6) What is meant by Orbital Mechanics?

7) Write about the requirement of Space Mission communication?

8) What do you mean by Mach number independence?

9) What are standard operation practices?

10) What is “SPIN- STABILIZATION?

PART.B

11. Derive and explain about the Two- Dimensional trajectories of the Rockets? (OR)

12. Explain about the following A) Impact point calculation B) Flight dispersions 13. Derive the Orbit equation with neat sketches? .

(OR) 14. Discuss in detail about the Aero-braking and Lifting body Reentry

15) The semi major axis of a satellite when injected into the orbit has a semi major axis of 1.0478

earth radii and a period of 90.54 min. Calculate the mass of the earth in the units of the sun’s mass

(OR)

16) A satellite transfers from a low circular orbit or radius 7000 km to a circular orbit with a period of 12 hours. (a) What is the radius of final orbit? (b) If a Hohmann transfer is used, calculate the eccentricity of the transfer ellipse and total velocity increment.

17) Explain in detail about the Semi-rigid spacecraft?

(OR) 18). Discuss about the Gravity gradient satellite with neat sketches?

19) Distinguish the difference between the Spin stabilization and dual spin stabilization attitude control mechanisms for the space craft?

(OR) 20) Explain in detail about the satellite control networks and their working procedure?








PART-A

1) What do you know about the interplanetary probes?

2) What is Sounding Rocket?

3) What is meant by Exponential atmosphere?

4) Explain about the entry trajectory on a velocity-altitude map?

5) Write about the conic section geometry?

6) Explain about the long-range function?

7) Define the orbital elements?

8) Write about Ballistic parameter?

9) What is meant by solar radiation torque?

10) Write the advantages of glide entry?

PART-B

11). Explain in detail about the Radiation effects and Launch environment? B) What do you know about the a) Charged particle motion b) VAN ALLEN belts?

(OR) 12 Explain in detail about the factors do we consider for selecting a commercial launch vehicle?

13). Derive the equation for the high temperature flow field around a blunt body (OR)

14) Show that for μ = 0.5, the curves are symmetric about y‐axis also and that the points L1,L2 are reached Simultaneously when constant C is continuously decreased starting with a very large initial value.

Compute the position of the five Lagrange points in the case μ = 0.5. 15) The earth’s mean heliocentric velocity is 29.78 km/s. Assume that meteors travel in parabolic Heliocentric orbits. Show that the speed of approach of meteors towards earth lies between 12.3 and

71.9 km/s. (OR)

16) Determine the orbital period of a spacecraft whose perigee and apogee are at an altitude of 122 km And 622 km, respectively

17) Show that the period of an orbit close to the surface of a homogeneous spherical planet is a function

of planetary density only (OR)

18) A satellite transfers from a low circular orbit or radius 7000 km to a circular orbit with a period of 12 hours. (a) What is the radius of final orbit? (b) If a Hohmann transfer is used, calculate the eccentricity

of the transfer ellipse and total velocity increment.(c) Is it possible to achieve fuel economy using belliptic 3 impulse transfer instead

(OR)

19) The motion of a spinning rigid satellite in the absence of external torque is given by

] 20) Prove that the equation of a satellite pitching motion in a circular orbit is given by

Find the approximate period of oscillations for motion in small. Integrate this equation to determine the

first integral of pitching motion. Hence find the maximum pitching angle for the case when initial Pitch angle is zero while initial pitching velocity (dimensionless) is 3 / 2 and ki=1.




MODEL PAPER-IV Time: 3 hours Marks: 75




PART-A

1) What do you know about the charged particle motion?

2) What are the types of injectors?

3) Write short notes on the effect of ambient pressure on nozzle flow in case of rocket?

4) Explain about the multi stage rocket?

5) Write about the parallel staging and multi staging?

6) Explain about entry problem?

7) Explain about the true anomaly and flight path angle?

8) Write about the Attitude actuators?

9) What are the different types of solar cell types?

10) What do you know about the space power system?

PART B

11) Derive the equation for the parallel staging rocket and series staging rocket? (OR) 12) Explain in detail about the Trade off ratios and vehicle sizing in detail with neat sketches? 13) Derive the maximum deceleration for the straight line ballistic entry trajectory? (OR) 14) Explain in detail with equations about the Re-entry dynamics? 15)

16) 17) 18)A) Derive equation for the YO-YO mechanism B) Explain about the Gravity-gradient torques on closed earth satellite? 19) A) Explain in detail about the Mission phases and core operations? B) Explain in your view about the standard operation practices 20)

1

FLIGHT MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)


FLIGHT MECHANICS-I (R13)

MODEL PAPER – I

MAXIMUM MARKS: 75




1) Define lift , drag and side force (3M)

2) Define specific air range and specific endurance (3M)

3) Define specific excess power (2M)

4) Explain about the CTOL –conventional take-off and landing (3M)

5) Write a short note on OEW or APS (2M)

6) Explain about performance planning or the operating data manual(ODM) (2M)

7) Define specific fuel consumption (2M)

8) There are two categories of structural limitations in airplane design what are they explain

them (3M)

9) Explain about the fuel planning (3M)

10) What is one-engine- inoperative cruise ceiling (2M)

PART B Max Marks: 50



11) Explain the factors to be considered in the estimation of performance of an aircraft and

how the estimation is carried out

OR

12) Describe the mission of a military aircraft with the required sketches

13) Derive an expression for range and endurance for aircraft with thrust producing engines

and explain the cruising method of constant angle of attack and constant mach number

OR

14) Discuss cruise performance measurement and climb performance measurement using

parametric performance data analysis

2


15) Explain the equations of motion of an aircraft with thrust producing engines in a climb

.Derive the expressions for climb gradient and climb rate

OR

16) (a)Describe the phases of descending flight through a diagram and

(b) Discuss the various criteria that govern the manner in which the aircraft is flown in

each phase

17) Explain the process of take –off with the help of a diagram and discuss how take-off

distances are estimated

OR

18) Discuss the space available and space required for take – off performance

19) Discuss block diagram and payload range diagram used in making performance summary

OR

20) Discuss the determination of the field length available for take –off ,all engines operating

(AEO) and one – engine inoperative (OEI)

3




MODEL PAPER – II

MAXIMUM MARKS: 75




1) Explain about the service and absolute ceiling (2M)

2) Explain about the geopotential and geometric altitude (2M)

3) Define induced drag and wave drag (2M)

4) Explain about the effect of alternative fuel flow laws (3M)

5) Discuss about the climb gradient and climb rate for aircraft with thrust producing

engines (3M)

6) Define specific total energy Es (2M)

7) Discuss minimum control speed ground Vmcg (2M)

8) Explain about the diversion fuel , reserves and tankering (3M)

9) Discuss about the correction to rate of climb for weight and temperature (3M)

10) Explain operational analysis (3M)




11) For international standard atmosphere , explain variation of temperature , pressure

variation with altitude with the help of neat and proper diagram .Also define lapse

rate ,stratosphere and troposphere

OR

12) Explain minimum drag speed minimum power speed and describe their importance in

aircraft performance studies

4


13) Derive Breguet range equation and discuss about the constant altitude , constant mach

number

OR

14) Discuss the comparison of cruise methods and explain through diagrams how range

function and endurance function vary with relative speed

15) What are the reasons for the maneuver performance of an aircraft to be limited by the

structural strength of the airframe? Discuss the main elements of a typical maneuver

envelope with the help of a schematic diagram

OR

16) Describe the equations of motion of an aircraft undergoing lateral maneuver or level

turn and derive an expression for radius of turn. Discuss with the help of a diagram

the maneuver boundaries for turning performance

17) Explain the process of landing with the help of a diagram and discuss the estimation

of the landing distances

OR

18) Define the performance classes used to classify aircraft in meeting the requirements

of certificate of airworthiness. what are the issues relating to discontinued landing

19) What are the purposes for which the performance of an aircraft needs to be measured

in flight? Explain the parametric forms for aerodynamic forces and thrust with the

help of a diagrams

OR

20) What is the purpose of flight planning ?How performance data have to be organized

and presented to meet the requirements of flight planning and in particular for

performance planning and fuel planning

5




MODEL PAPER – III

MAXIMUM MARKS: 75




1) Define airspeed indicator reading, Indicated airspeed and calibrated airspeed (3M)

2) Explain about the inertial forces , gravitational forces and aerodynamic forces (3M)

3) Derive the expression for endurance for jet propelled airplanes (3M)

4) Discuss about the cruise performance with mixed power plants (3M)

5) Write a short note on noise limitations (2M)

6) Explain about the effect of wind on descent performance (3M)

7) Explain VTOL and STOL (2M)

8) The total fuel load for the mission can be broken down in to three parts what are they

explain them in single sentences (2M)

9) What is performance data reduction (2M)

10) Explain marketing and fleet selection (2M)




11) What for aircraft performance measurement is required ?Show with the help of diagrams

typical military aircraft mission profiles

OR

12) Discuss aircraft force system needed for formulating the performance equations of

motion

13) Derive an expression for range and endurance for aircraft with thrust producing engines

OR

14) Discuss about the effect of WAT (weight, altitude ,and temperature ) on cruise

performance

15) Explain about the measurement of best climb performance (b)Discuss descent

performance in aircraft operations

6


OR

16) (a)Explain about the transport aircraft maneuver performance and military aircraft

maneuver performance

(b) Determine the load factor, bank angle turn radius for an aircraft in a level turn at a

true speed of 120km and a turn rate of 15deg/s

17) What are the phases into which the flight is divided for the purpose of flight planning

?Explain with the help of diagram the airfield distances available for take-off

OR

18) (a)Explain the effect on the take-off distances of the flight variables

(b) Find lift to drag ratio when drag coefficient at zero lift is 0.2 density of air at 10 km is

0.4135kg/cubic meter and speed of aircraft is 300kmph.The mass of the aircraft is

5000kg area of wing plan form is 5sqm and its AR is 6, span efficiency factor is 1

19) Explain about the cruise performance and also the corrections to cruising speed for

weight and temperature

OR

20) (a) Explain certification (b) Explain the additional performance summary data

7




MODEL PAPER – IV

MAXIMUM MARKS: 75




1) What is ISA (2M)

2) Explain the significance of load factor (2M)

3) Distinguish between troposphere and stratosphere (2M)

4) Write the formula thrust required and thrust available (2M)

5) Which is the main parameter affecting rate of climb (2M)

6) Write down the formula to calculate the take –off distances (3M)

7) Define fuel weight in aircraft (3M)

8) What are the segments in the take –off performance and landing performance (3M)

9) What is VN diagram or maneuver envelope (3M)

10) Write about TOW, MTOW, MSP and MFC (3M)




11) (a) Discuss vertical structure of the atmosphere and its various layers through a diagram

(b) Explain air data computer system using a diagram

OR

12) Derive the expression for drag polar and also explain about the drag reduction methods

with requires figures

13) (a) An aircraft with wing loading of 1500N/sqm is gliding from an altitude of 4 km. What

is the glide angle corresponding to minimum rate of descent. If zero lift drag coefficient

is 0.2? what is the equilibrium glide velocity associated with the descent

(b) Write shortly about the climbing flight and also write short notes on weight estimation

of the aircraft

OR

8


14) Write short note on the endurance of an aircraft and derive the expression for both

turbojet and propeller driven airplanes

15) (a) An F-22 is performing a 5-g pull up at 10,000 ft and 500 kn true airspeed what is the

turn rate and turn radius

(b) Explain about the effect of wind on climb and descent performance

OR

16) Derive an expression for specific excess power

17) Explain about the take –off performance showing with the illustration of ground roll

,airborne distance and total take –off distance and also explain with the intermediate

segments of the ground roll

OR

18) Calculate total take off distance for Gulfstream _like airplane at standard sea level

assuming a take-off gross weight of 73,000lb .The design features of the airplane are

s=950ft2,AR=5.92,Cdo=0.015and K= 0.08with the added information that the wing span

is 75ft .Assume that the variation of engine thrust with the velocity during takeoff is

given by equation (6.74) .where k*1=27,700 lb k

*2=21.28lb s/ ft

2 and k

*3=1.117x10

-2 lb s/

ft2.

The height of the wing above the ground during the ground roll is 5.6ft.Assume the

runway is dry concrete ,with μr=0.04(example 6.6 in aircraft performance J.D ANDERSON)

19) Explain about fuel planning , performance planning and the contents of the performance

manual

OR

20) Explain about block performance and flight planning

9




MODEL PAPER – V

MAXIMUM MARKS: 75




1) Explain with the sketch the civil transport aircraft flight profile (3M)

2) Write a short note on measurement of Mach number (2M)

3) Define cruise –climb technique and note the equation for cruise method 1 (3M)

4) What is effect of alternative fuel flow laws in cruising performance (3M)

5) Define pull up maneuver (3M)

6) Define flare distance (2M)

7) Define payload in aircraft and write the conditions for un accelerated steady level flight

(3M)

8) Write a short note on gliding flight (2M)

9) What is discontinued landing and the space available (2M)

10) Explain about the rotation speed and the decision speed (2M)




11) (a)Explain about the off standard and design atmosphere (b)Explain about the pressure

height relation ship

OR

12) Derive the equations of motion for steady level flight

13) (a)Explain about the air data computers with the required sketches

(b)Define range, endurance, the drag force, the side force and the overall drag force D

OR

14) (a)Explain about the cruising performance with the comparison of three cruise technique

methods

(b) Estimate the maximum range at 30,000ft for the gulfstream IV. Also calculate the

flight velocity to obtain this range. The maximum usable fuel weight is 29,500 lb .The

10


thrust specific fuel consumption of the Rolls Royce Tay turbofan at 30,000 ft is 0.69 lb of

fuel consumed per hour per pound of thrust (example 5.19 aircraft performance J.D ANDERSON)

15) Derive the expression for maximum turn radius and maximum turn rate

OR

16) Derive the expression for rate of climb and also explain the graphical approach

17) (a)Explain about the V-n diagram with neat sketch

(b)Explain about the landing performance with neat sketch

OR

18) (a)Explain baulked landing (b) Discuss air safety procedures and requirements on

landing performance

19) Explain the purpose of performance measurement in flight

OR

20) Explain performance summary for fleet selection and payload range diagram with

required fig

course coverage summary and question bank … banks/ae/ii ane ii sem q.bank 2016... · course...

Documents