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# MCQs on Flight Mechanics – Steady Level Flight-2

Following diagram represents ____________

a) thrust required curve

b) lift curve

c) drag polar

d) lift polar

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a

Explanation: Above diagram is showing a typical Thrust required curve. Variation of Thrust required can be observed in the diagram. Lift curve is showing the relationship between lift and angle of attack. Drag polar is showing the graphical representation of the aircraft drag characteristics.

Following diagram represents _________

a) lift induced thrust required

b) zero lift thrust required

c) drag polar

d) lift curve

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a

Explanation: Para below it Lift induced thrust required is shown in the diagram. Lift induced thrust required and zero lift thrust required are not equal, they are two different properties. Lift curve and drag polar is used to provide information of the lift variation and drag variation respectively.

Calculate how much power will require to maintain cruise speed of 120 m/s if thrust required is 1KN. Consider steady level flight.

a) 120KW

b) 110N

c) 120N

d) 129W

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a

Explanation: Power = thrust*velocity = 120*1 = 120KNm/s = 120KW.

An aircraft has L/D as 12 and thrust required at this value is 100N. Now if L/D has doubled then what will be the new thrust required?

a) 50N

b) 500N

c) 100 N

d) 12.5N

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a

Explanation: Given, 1: L/D = 12 and thrust required T1 = 100N

Now, L/D is doubled. Hence, new thrust required T2 = T1*(old L/D) / (New L/D)

= 100*12/2*12 = 100*12/24 = 50N.

An aircraft is operating with CL of 1.5 and has power required of 120W. If we want to reduce the power required by half then, find the value of CL at this power required condition. Consider steady level flight.

a) 2.38

b) 1.946

c) 9.45

d) 5.59

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a

Explanation: Given, P1 = 120W, CL1 = 1.5, P2 = P1/2 = 120/2 = 60W.

Now, CL for new Power required P2 is given by,

CL2 = CL1*[P1/P2](2/3)

= 1.5*[120/60](2/3) = 2.38.

Following diagram represents ________

a) altitude effect on power required

b) altitude effect on thrust

c) drag polar

d) lift curve

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a

Explanation: Above diagram is showing a typical power required graph. Above diagram is showing the altitude effects on the power required. Altitude effects on the thrust required will be different from the power required. Drag polar will show drag properties variation with lift. Lift curve is used to represent lift coefficient variation with AOA.

If power required at sea level altitude is 2005W then, determine power required at altitude at which density ratio is 0.9.

a) 2.113KW

b) 211115W

c) 2354W

d) 500W

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a

Explanation: Power at altitude = Sea-level power*[1/density ratio]0.5

= 2005*[1/0.9]0.5 = 2113.45W = 2.113KW.

Determine the value of drag at which we can have minimum power if given reference area is 10m2 and zero lift drag coefficient is 0.5. Consider q as 120Pa.

a) 2400N

b) 1.25

c) 9.85

d) 4500 KNs

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a

Explanation: Drag at minimum power = q*area*[4*zero lift drag coefficient] = 120*10*4*0.5 = 2400N.

Find the value of lift coefficient to ensure power required minimum condition for cruise if CD0/K is given as 0.480.

a) 1.2

b) 2.1

c) 1.7

d) 7.5

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a

Explanation: Lift coefficient = [3*CD0/K]0.5

= [3*0.480]0.5 = 1.2.

Find instantaneous range of a jet propelled aircraft if lift to drag ratio is 12 and weight fraction at cruise W1/W0 is 1.9. Consider cruise speed of 120m/s and SFC of 0.00161 per second.

a) 574km

b) 574m

c) 574miles

d) 574ft

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a

Explanation: Range = (lift to drag)*(speed/SFC)*ln (W1/W0)

= 12*(120/0.00161)*ln (1.9) = 574Km.

An aircraft has maximum lift to drag ratio of 15. If we want to fly aircraft for best range then, find the best value of aerodynamic efficiency to achieve above mentioned result.

a) 12.9

b) 13.5

c) 15

d) 12.1

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a

Explanation: Aerodynamic efficiency for best range = 0.866*[maximum lift to drag]

= 0.866*15 = 12.9.

A propeller aircraft has wing loading of 30 unit and is operating with density of 1.21 unit. Determine velocity for maximum loiter. Consider K/CD0 as 0.1.

a) 3unit

b) 5unit

c) 9unit

d) 10unit

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a

Explanation: Maximum loiter velocity = 2∗wingloading∗K3CD0√density−−−−−−−−−−−−−−√

= 2∗30∗0.1/3√1.21−−−−−−−−√=49.58∗0.1816−−−−−−−−−−−√ = 3 unit.

A prop driven aircraft has propeller efficiency of 0.92 and C as 0.000745 1/m. If lift to drag ratio is 14 and weight fraction as 1.145 then, find range of the propeller driven aircraft.

a) 2340.95m

b) 2340.5miles

c) 2340km

d) 2500miles

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a

Explanation: Prop range = (lift to drag)*[propeller efficiency/C]*ln (weight fraction)

= 14*[0.92/0.000745]*ln (1.145) = 2340.95m.

A jet engine is designed to operate at endurance of 12hrs. If weight fraction is 1.6 and jet engine has tsfc C as 0.00021 per second then, find at which lift to drag ratio that can satisfy above criteria.

a) 19.3

b) 18

c) 12

d) 12.6

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a

Explanation: Lift to drag ratio = Endurance*C/ln (weight fraction)

= 12*3600*0.00021 / ln 1.6

= 9.072/0.47 = 19.3.

In Steady level unaccelerated flight, lift is equal to weight.

a) True

b) False

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a

Explanation: In steady level unaccelerated flight, lift is equal to weight of the aircraft. Drag is equal to Thrust of the aircraft. This is also called cruise flight. For steady level unaccelerated flight, Lift = weight = q*S*CL