II B.TECH II SEMESTER –
AERONAUTICAL ENGINEERING
FLIGHT MECHANICS-I (R13)
MODEL PAPER – I
MAXIMUM MARKS: 75
PART A Max
Marks: 25
i.
All
questions in this section are compulsory
ii.
Answer
in TWO to FOUR sentences.
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1)
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Define lift , drag and side
force
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(3M)
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2)
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Define specific air range and
specific endurance
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(3M)
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3)
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Define specific excess power
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(2M)
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4)
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Explain about the CTOL
–conventional take-off and landing
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(3M)
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5)
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Write a short note on OEW or
APS
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(2M)
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6)
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Explain about performance
planning or the operating data manual(ODM)
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(2M)
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7)
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Define specific fuel
consumption
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(2M)
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8)
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There are two categories of
structural limitations in airplane design what are they
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explain
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them
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(3M)
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9)
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Explain about the fuel planning
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(3M)
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10) What is
one-engine- inoperative cruise ceiling
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(2M)
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PART
B Max
Marks: 50
i.
Answer
only one question among the two questions in choice.
ii.
Each
question answer (irrespective of the bits) carries 10M.
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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)
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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II
B.TECH II SEMESTER – AERONAUTICAL ENGINEERING
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FLIGHT
MECHANICS-I (R13)
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MODEL PAPER – II
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MAXIMUM
MARKS: 75
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PART A
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Max Marks: 25
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i.
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All questions in this section
are compulsory
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ii.
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Answer in TWO to FOUR
sentences.
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1)
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Explain about the service and
absolute ceiling
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(2M)
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2)
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Explain about the geopotential
and geometric altitude
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(2M)
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3)
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Define induced drag and wave
drag
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(2M)
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4)
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Explain about the effect of
alternative fuel flow laws
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(3M)
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5)
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Discuss about the climb
gradient and climb rate for aircraft with thrust producing
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engines
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(3M)
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6)
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Define
specific total energy Es
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(2M)
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7)
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Discuss
minimum control speed ground Vmcg
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(2M)
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8)
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Explain about
the diversion fuel , reserves and tankering
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(3M)
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9)
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Discuss about the correction to
rate of climb for weight and temperature
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(3M)
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10) Explain operational
analysis
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(3M)
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PART
B Max
Marks: 50
i.
Answer
only one question among the two questions in choice.
ii.
Each
question answer (irrespective of the bits) carries 10M.
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
II B.TECH II SEMESTER –
AERONAUTICAL ENGINEERING
FLIGHT MECHANICS-I (R13)
MODEL PAPER – III
MAXIMUM MARKS: 75
PART A Max
Marks: 25
i.
All
questions in this section are compulsory
ii.
Answer
in TWO to FOUR sentences.
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1)
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Define airspeed indicator
reading, Indicated airspeed and calibrated airspeed
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(3M)
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2)
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Explain about the inertial
forces , gravitational forces and aerodynamic forces
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(3M)
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3)
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Derive the expression for
endurance for jet propelled airplanes
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(3M)
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4)
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Discuss about the cruise
performance with mixed power plants
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(3M)
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5)
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Write a short note on noise
limitations
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(2M)
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6)
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Explain about the effect of
wind on descent performance
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(3M)
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7)
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Explain VTOL and STOL
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(2M)
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8)
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The total fuel load for the
mission can be broken down in to three parts what are they
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explain them in single
sentences
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(2M)
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9)
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What is performance data
reduction
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(2M)
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10) Explain
marketing and fleet selection
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(2M)
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PART
B Max
Marks: 50
i.
Answer
only one question among the two questions in choice.
ii.
Each
question answer (irrespective of the bits) carries 10M.
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
II B.TECH II SEMESTER –
AERONAUTICAL ENGINEERING
FLIGHT MECHANICS-I (R13)
MODEL PAPER – IV
MAXIMUM MARKS: 75
PART A Max
Marks: 25
i.
All
questions in this section are compulsory
ii.
Answer
in TWO to FOUR sentences.
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1)
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What is ISA
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(2M)
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2)
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Explain the significance of
load factor
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(2M)
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3)
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Distinguish between troposphere
and stratosphere
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(2M)
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4)
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Write the formula thrust
required and thrust available
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(2M)
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5)
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Which is the main parameter
affecting rate of climb
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(2M)
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6)
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Write down the formula to
calculate the take –off distances
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(3M)
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7)
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Define fuel weight in aircraft
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(3M)
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8)
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What are the segments in the
take –off performance and landing performance
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(3M)
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9)
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What is VN diagram or maneuver
envelope
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(3M)
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10) Write
about TOW, MTOW, MSP and MFC
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(3M)
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PART
B Max
Marks: 50
i.
Answer
only one question among the two questions in choice.
ii.
Each
question answer (irrespective of the bits) carries 10M.
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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/ ft2 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
II B.TECH II SEMESTER –
AERONAUTICAL ENGINEERING
FLIGHT MECHANICS-I (R13)
MODEL PAPER – V
MAXIMUM MARKS: 75
PART A Max
Marks: 25
i.
All
questions in this section are compulsory
ii.
Answer
in TWO to FOUR sentences.
|
1)
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Explain with the sketch the
civil transport aircraft flight profile
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(3M)
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2)
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Write a short note on
measurement of Mach number
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(2M)
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3)
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Define cruise –climb technique
and note the equation for cruise method 1
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(3M)
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4)
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What is effect of alternative
fuel flow laws in cruising performance
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(3M)
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5)
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Define pull up maneuver
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(3M)
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6)
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Define flare distance
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(2M)
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7)
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Define payload in aircraft and
write the conditions for un accelerated steady level flight
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(3M)
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8)
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Write a short note on gliding
flight
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(2M)
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9)
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What is discontinued landing
and the space available
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(2M)
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10) Explain
about the rotation speed and the decision speed
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(2M)
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PART
B Max
Marks: 50
i.
Answer
only one question among the two questions in choice.
ii.
Each
question answer (irrespective of the bits) carries 10M.
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
FLIGHT
MECHANICS-I B.TECH - II-II (AERONAUTICAL ENGG)
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
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