FLIGHT MECHANICS AERONAUTICAL ENGINEERING R13 Important Questions

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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.

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

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)

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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
	FLIGHT MECHANICS-I (R13)
	MODEL PAPER – II
	MAXIMUM MARKS: 75
PART A	Max Marks: 25
i.	All questions in this section are compulsory
ii.	Answer in TWO to FOUR sentences.
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)

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)

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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)

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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.

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)

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)

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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)

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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.

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)

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)

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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,C_do=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/ ft^2.The height of the wing above the ground during the ground roll is 5.6ft.Assume the

runway is dry concrete ,with μ_r=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)	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)

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)

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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