Module 8

7/17/2019 Module 8

http://slidepdf.com/reader/full/module-8-568c53f5690ba 1/32

1. Which of the following is correct for atmosphere?a. Its pressure and density decreases with increasing

heightb. Its pressure and density increases with increasing height

c. Its pressure decreases and its density increases withincreasing height

2. Which layer of atmosphere is the lowest one?a. Stratosphereb. Ionespherec. Troposhere

3. Which atmosphere layer does most of the conventional

ights ta!e place in?a. Troposhereb. Stratospherec. Ionesphere

". What is the height di#erence in troposhere caused by?a. $i#erent air contentsb. Temperature and gravity di#erencesc. %entrifugal force di#erence

&. Which of the following about atmosphere layers is correct?a. The layer between troposphere and stratosphere is

called e'osphereb. The stratosphere is characterised by the absence of

weather and smooth ying conditionsc. The ionosphere consist of atomised hydrogen and

helium( whereas hydrogen is predominating element

7/17/2019 Module 8


). What is the content amount of nitrogen in dry air at sea

level?a. *+,b. 21*

c. *1

+. Which of the following is correct?a. The higher the temperature is the more water vapour

can be retained by airb. The lower the temperature is the more water vapour

can be retained by air

c. There is no de-ned relation between temperature andwater vapour

,. Which of the following describes the humidity?a. The amount of temperature enough for rainingb. The amount of water present in the airc. The capacity to absorb water by air

. What is the relation between relative humidity and the air

density?a. / high relative humidity decreases the density of

a#ected airb. 0elative humidity is a ratio of density of substance to

density of waterc. / high relative humidity increases the density of

a#ected air

1. What de-nes the atmospheric pressure?a. $ensity of air over a given areab. Weight of air over a given areac. Weight of air times altitude

7/17/2019 Module 8


11. What is the reference for the variations in atmosphere

at di#erent latitudes and altitudes de-ned by I%/?a. IS/

b. S4c. IS

12. Which of the following de-nes the relation between

atmospheric pressure and altitude?a. /tmospheric pressure stays stable while altitude

changes

b. /tmospheric pressure increases in increasing altitudec. /tmospheric pressure decreases in increasing altitude

13. What is temperature value at S4 according to the

IS/?a. 5%b. 1&5%c. 2&5%

1". What is the I%/ Standard air pressure at S4?a. 112.2& in h6ab. 113.2& in h6ac. 131.1& in h6a

1&. What is the I%/ Standard air density at S4?a. 1.2" !g7m8b. 1 !g7dm8c. 113 g7m8

7/17/2019 Module 8


1). What is the temperature gradient from S4 up to an

altitude of appro'. 11 !m?a. 9).&5% per 1. feetb. 925% per 1. meter

c. 9).&5% per 1. meter

1+. Which can be said for the temperature at an altitude

of 1,. m?a. ore than 9&).&5%b. 4ess than 9&).&5%c. /t 9&).&5%

1,. Which of the following can be said for temperature

change in atmosphere depending on the altitude?a. Temperature increases by increasing altitudeb. Temperature decreases up to an altitude of 11 !m and

stays stable between 11 !m and 2 !m and then starts

to increasec. Temperature increases up to an altitude of 11 !m and

stays stable between 11 !m and 2 !m and then starts

to increase again

1. What is the appro'imate ratio of the air pressure at

11 !m to the air pressure at S4?a. :b. 17,

c. 172

2. Which of the following can be said for total energy of

the air?a. It increases with increasing !inetic energyb. It increases with decreasing potential energyc. It e;uals to the sum of !inetic energy and potential

energy

7/17/2019 Module 8


21. If the total amount of energy stays constant( any

increase in !inetic energy will cause<

a. /n e;ual increase in potential energyb. /n e;ual decrease in potential energyc. The potential energy to stay constant

22. /ccording to the =ernoulli>s principle( what happens

to the pressure and velocity of air in narrow part of enturi

tube comparing wide part?a. ore pressure and more velocityb. ore pressure and less velocityc. 4ess pressure and more velocity

23. What is the static pressure of air caused by?a. oving airb. Still airc. oving air subtracted from still air

2". Which of the following is correct?a. /ny ob@ect in still air will e'perience an additional

pressure in all directionsb. /ny ob@ect in moving air will e'perience an e;ual

pressure in all directionsc. /ny ob@ect in moving air will e'perience an additional

pressure in the direction of motion of air

2&. What happens to the dynamic pressure of air if the

velocity is doubled?a. Aour times more than beforeb. Two times more than beforec. Two times less than before

7/17/2019 Module 8


2). Which statement is wrong for airfoil?a. / symmetrical airfoil has the same curve on each side of

the chord lineb. Bpper side is larger than the lower in symmetrical airfoil

c. Shapes of top and bottom side of an asymmetrical airfoilare di#erent

2+. Which comparison is correct for asymmetrical and

symmetrical airfoils?a. When the angle of attac! is increased( center of

pressure in symmetrical airfoil moves toward the

leading edge but stays at the same point inasymmetrical airfoil

b. When the angle of attac! is increased( center of

pressure in asymmetrical airfoil moves toward the

leading edge but stays at the same point in symmetrical

airfoilc. When the angle of attac! is increased center of pressure

moves toward the leading edge both in symmetrical and

asymmetrical airfoils

2,. Aor most airfoils the ma' angle of attac! lies

between<a. 1&5 9 25b. 15 9 1&5

c. 25 9 2&5

2. Which is wrong for boundary layer?a. It is important to !eep it as thic! as possibleb. /bove ma' angle of attac! total seperation of boundary

layer occursc. 0andomly owing air on the surface is called boundary

layer

7/17/2019 Module 8


3. Which term may be used for all types of pro-le drag?a. Induced dragb. 6arasite dragc. Wave drag

31. What de-nes form drag?a. It is obtained when induced drag is subtracted from

pressure dragb. It is the additional drag when the wing is producing liftc. It is the sum of all aerodynamic forces

32. Aorm drag can be considerably reduced by<a. Increasing liftb. Increasing //

c. Streamlining

33. Which condition is called Cadverse pressure gradient>?a. Thic!ening the boundary layer further bac! along the

wingb. $ecreasing of air pressure with increasing altitudec. $ecreasing of air pressure with increasing velocity in

enturi tube

3". What is the main reason causing boundary layer

occur?a. =ecause the velocity of air on upper surface is more

than the velocity of air on lower surfaceb. =ecause air is viscous and it tends to stic! to the aircraft

s!in

7/17/2019 Module 8


c. =ecause airfoils has a curve on upper surface and that

causes the air to turbulate

3&. When the total drag of an aircraft is calculated( total

drag is found to be greater than the sum of the drags of

indiviuals. Dow can this di#erence be e'plained?a. Interference drag caused by @unction areasb. Aorm drag caused by sharp parts of structure

c. Induced drag increased with increasing lift

3). Intereference drag can be reduced by<a. 6olishingb. Increasing the velocityc. Aairing the @unctions

3+. Why are wing tip vortices formed?a. When the altitude is too high( air is turbulenced easily

due to the decreased density of airb. =ecause of pressure di#erence between upper surface

and lower surfacec. =ecause of the surface roughness caused by dirt( rivet

etc.

3,. When the lift is increased<a. 6ressure di#erence between top and bottom surfaces

decreasesb. The strength of vorte' decreasesc. Induced drag increases

3. 6ressure drag is sum of..

7/17/2019 Module 8


a. Aorm drag and induced dragb. Wave drag and induced dragc. 6arasite drag and wave drag

". Which is wrong about air movement?a. The air @ust ahead of the wing has an upward

component( called upwashb. The movement of the air @ust behind of the wing has an

downward component( called downwashc. The movement of the air @ust ahead of the wing has an

downward component( called upwash

"1. / bunch of air circulating around itself at the wing tips

and trailing edges is called<a. =oundary layer

b. orte'c. 4aminar air ow

"2. In which parts of airfoil is stagnation line highly

possible to be found?a. Bpper surface and lower surfaceb. 0oot and tip of airfoilc. 4eading and trailing edges of airfoil

"3. What is the relation between taper ratio and stall

speed?a. When the taper is increased( the stall characteristic

becomes adverseb. When the taper ratio is decreased( the stall speed

decreases

c. There is no relation between taper ratio and stall speed

7/17/2019 Module 8


"". Which statement is correct for -neness ratio?a. The higher the speed( the greater should be the

-neness ratiob. The lower speed( the greater should be the -neness

ratioc. Aineness ratio should be constant for any type of airfoil

at any wor!ing speed

"&. Aineness ratio of a body<a. The ratio of wing width at the wing root to wing widht at

the wing tip

b. The ratio of wing length to the wing widthc. The ratio of length to diameter of streamlined shaped

"). What de-nes mean camber line?a. The shortest distance from leading edge to trailing edge

in asymmetrical airfoilsb. / line drawn in the middle between the upper and lower

surfacesc. The longest height from upper surface to lower surface

"+. Which of the following is a correct statement?a. ean chord line is always straight @ust li!e mean camber

lineb. If the mean camber line and mean chord line are

identical( the wing is symmetrical wingc. ean camber line is the shortest distance from leading

edge to trailing edge in asymmetrical airfoils

",. Which statement is incorrect for mean aerodynamic

chord?a. / line where all aerodynamic and gravitational forces

mathematically act upon

b. It is used as reference for center of gravity calculationsc. It can not be used for aerodynamic calculations

7/17/2019 Module 8


". Which of the following is incorrect for center of

pressure?

a. %6 is the point on chord line of an airfoil at which all ofaerodynamic forces are concentrated

b. %6 of a subsonic airfoil is located at appro'. 39"* of

the mean chord line bac! from the trailing edge in level

ightsc. n a symmetrical airfoil %6 doesnt move when the angle

of attac! changes

&. What de-nes the angle of attac!?a. The angle between resultant force of lift and drag

forces( and the chord lineb. The angle between chord line and the direction of air

movementc. The angle of incidence from wing root to wing tip

&1. Which of the following statements is correct?a. Wash in is a twist in the wing that increases its angle of

incedence near the tipb. Wash out is a twist that decreases the angle of

incidence near the wing rootc. Swept bac! wings e'perience a wash in and an increase

of lift at their tips

&2. Which of the following statements about forces is

incorrect?a. In ight with unchanged power settings( thrust

increases as weight decreasesb. The amount of lift re;uired to !eep the aircraft in level

ight decreases as weight decreasesc. Thrust must be always bigger than drag so that the

aircraft has a velocity

7/17/2019 Module 8


&3. Which statement for lift is not correct?a. 6ressure di#erence between upper and lower surfaces

causes the airfoil to be liftedb. The airfoil is said to achieve *)& of the lift from lower

surface and *3& from upper surfacec. The sum of all lifting forces are considered to act upon

an imaginary point !nown as the center of pressure

&". What happens beyond the critical angle of attac!?a. The lift coeEcient and drag coe-cient both starts to

increaseb. Fo lift can be produced any longer and the airfoil stallsc. While the lift reaches its pea! value( the drag coeEcient

stays stable

&&. When the airspeed is doubled<a. The lift will increase by a factor of two

b. The drag will decrease by a factor of twoc. The lift will increase by a factor of four

&). When the angle of attac! is increased<a. The lift will decreaseb. The lift will increasec. The lift will stay stable

&+. %lear ice usually a product of temperature inversions

at a temperature..a. 0ange from 5% to 91&5%b. =elow 91&5%c. In all icing conditions

&,. Which of the following is not correct for mi'ed ice?

7/17/2019 Module 8


a. The rough rime ice crystals are covered by clear iceb. i'ed ice is a product of temperature range from 5% to

91&5%c. i'ed ice weighs more than rime ice and produces more

drag than clear ice

&. Which of the icing factors inuence the type of ice

formation?a. Temperature and speedb. $roplet siGe and temperaturec. Speed and droplet siGe

). Which of the following is correct for icing factors?a. Ice collects more eEciently on larger airfoilsb. The higher airspeed the lesser the ice build9upc. The larger water droplets the lesser the ice buildup

)1. Which force directly !eeps the aircraft in the air?a. Thrustb. Weight

c. 4ift

)2. Which of the following is correct?a. 4ift can only be produced if the aircraft is moving

forwardb. Thrust is not needed to produce the lift( it is only for

speed of aircraft

c. In steady ight the lift force e;uals Gero

)3. Aor the aircraft to remain at the same altitude<a. /ll of main four forces must be e;ual to each otherb. The total forward force must be e;ual to the total

bac!ward forcec. The total upward forces must be e;ual total to the

downward forces

7/17/2019 Module 8


)". What causes the parasite drag?a. /ll aerodynamic forcesb. /ll factors not producing liftc. /dverse winds

)&. What is true for steady state ight at constant

altitude?a. Thrust must be higher than drag to !eep the aircraft at

constant speedb. Thrust must be e;ual to the dragc. The relation between thrust and drag doesnt ma!e any

di#erence for steady state ight

)). What !ind of moment does the thrust acting below

the center of gravity produce?a. / nose9up momentb. / nose9down momentc. / directional moment

)+. What !ind of moment does the drag acting above the

center of gravity produce?a. / nose9up momentb. / nose9down momentc. Arictional moment

),. What is the tas! of force acting on tail plane?a. =eing an aid for lift in order to overcome gravitational

forcesb. 6roducing and maintaining the e;uilibrium of the

momentsc. It decreases the e#ect of drag to improve the

e#ectiveness of thrust

). What can be said for the force on tail plane?

7/17/2019 Module 8


a. Its direction can be forward and bac!wardb. It needs to be small only because a small one is able

produce a large momentc. Its purpose is to prevent any force counteracting the

behaviour of the " main forces

+. Which force is not available during gliding?a. 4iftb. $ragc. Thrust

+1. Without thrust( the resultant of lift and drag must be

e;ual and opposite to the weight in gliding condition. What

is the corrective action to do that?a. Since there is no thrust there will no drag( then the

resultant force will be e;ual and opposite to weightb. Increasing the angle of attac! will increase lift so the

resultant force will be e;ual and opposite to weightc. Fose down con-guration is created in such a way that

weight will be opposite to the resultant force and

magnitudes will be the same

+2. Which mathematical e'pression is correct for gliding

angle?a. $74 H tanab. 47$ H tana

c. 47$ H sina

+3. What is the distance horiGontally ta!en by an aircraft

while descending from an altitude of 1.& feet to 1.

feet in gliding condition if the glide ratio is 11"?

7/17/2019 Module 8


a. 21. feetb. 1". feetc. +. feet

+". Jlide ratio is<a. The amount of loss of altitude versus distance gainedb. The ratio of thrust to dragc. The amount of distance gained versus the amount of

altitude gained

+&. What does the pilot need to do for level ight when

the engine has some reserve of power and throttle is

further opened?a. 6ushing the nose up slighlyb. 6ushing the nose down slightlyc. Trimming the elevator downward

+). Which of the following does not happen when the

aileron on the left wing moves down in a coordinated turn?a. Induced drag caused by the left aileron pulls the nose to

the leftb. 4eft wing moves upward because the lift on left wing is

higher than the lift on right wingc. The aircraft is rolled to the left

++. What should be done to compensate adverse yaw and

to yaw bac! the nose?a. $rag on lowered wing should be increased

b. elocity should be increased to increase total drag

7/17/2019 Module 8


c. The pilot should trim the rudder to the opposite

direction

+,. What de-nes the load factor?a. The ratio of the lift produced by wings to total weight of

aircraftb. The ratio of total weight of aircraft to the lift produced

by wingsc. The ratio of total load to the lift produced by wings

+. What is the load factor of an aircraft with a blan!angle of )5 ?a. 9.& gb. 1.) gc. 2 g

,. What is the load factor of an aircraft in level ight

condition?a. 1 gb. 1.) gc. 2 g

,1. Which statement about load factor is correct?a. / load factor of 1 g or greater is called negativeb. 4oad factor is the ratio of total weight to the lift

c. $uring a stall the load factor may be reduced towardsGero

,2. Stalls that occur with g forces on an aircraft are

called<

7/17/2019 Module 8


a. $isastrous stallb. 6owered stallc. /ccelerated stall

,3. The higher load factor in constant altitude turns

caused by the centrifugal force will<a. =alance the stall speedb. Increase the stall speedc. $ecrease the stall speed

,". Why are high9lift devices used in combination withairfoils?a. To be able to reach higher altitudesb. To support the e;uilibrium of momentsc. To reduce the ta!e9o# and landing speeds

,&. Which statement is not correct for aps?a. They increase the camber of airfoilb. They increase the ma'imum lift coeEcientc. They decrease the drag while increasing lift

,). Which type of ap slides outward and downward on

rails?a. Aowler apb. Split ap

c. 6lain ap

,+. What is the advantage of slotted aps on non9slotted

aps?a. They allow greater deection with smaller loss of liftb. They also increase drag while increasing lift at the same

time

c. They increase the stall speed by increasing angle ofattac!

7/17/2019 Module 8


,,. What is the advantage of slots?a. $ecreasing stall speedb. They have a lift9increasing e#ect even at low angles of

attac!

c. $ecreasing lift with increasing drag

,. When are the slats selected Cin> ?a. /t low angles of attac! and cruise speedb. /t high angles of attac! and slower speeds( e.g.

approach

c. n ta!e9o# and landing conditions

. Which of the following lift9augmentation aps is used

in modern aircraft?a. 6lain apsb. Split apsc. Aowler aps

1. Stability in pitch is called<a. 4ongitudinal stabilityb. 4ateral stabilityc. $irectional stability

2. Stability in roll is called<a. 4ongitudinal stabilityb. 4ateral stabilityc. $irectional stability

3. Stability in yaw is called<a. 4ongitudinal stabilityb. 4ateral stability

c. $irectional stability

7/17/2019 Module 8


". /fter a disturbance aircraft nose yaws bac! into

former position. What type of stability is achieved?

a. 4ongitudinal stabilityb. 4ateral stabilityc. $irectional stability

&. Which a'is of an aircraft is longitudinal stability

achieved about?a. 4ateral a'isb. ertical a'is

c. 4ongitudinal a'is

). Which a'is of an aircraft is lateral stability achieved

about?a. 4ateral a'isb. ertical a'isc. 4ongitudinal a'is

+. Which a'is of an aircraft is directional stability

achieved about?a. 4ateral a'isb. ertical a'isc. 4ongitudinal a'is

,. 4ongitudinal stability is achieved by<a. DoriGontal stabiliserb. ertical stabiliserc. /ileron

7/17/2019 Module 8


. $irectional stability is achieved by<a. DoriGontal stabiliserb. ertical stabiliserc. /ileron

1. 4ateral control is provided by<a. DoriGontal stabiliserb. ertical stabiliserc. /ileron

11. / wing and its dihedral construction provide<a. $irectional stability

b. 4ateral stabilityc. 4ongitudinal stability

12. /n aircraft>s propeller forces air to rotate around the

fuselage in a cor!screw9li!e manner. This causes the air to

stri!e the vertical -n and a sideways force. To prevent this

yawing force<

a. 4eading edge of vertical -n ofset a few degreeb. 0udder is trimmed to stabilise this forcec. 4eading edge ap is used to move it directly into the

relative wind

13. =y whom is the static stability performed?a. 6ilot

b. Technician on groundc. %onstruction

1". When the aircraft is is able to recover its original

steady ight path without re;uiring correction( static

stability is said to be<a. 6ositiveb. Fegative

c. Feutral

7/17/2019 Module 8


1&. When the aircraft( after displacement( maintains the

displaced attitude( static stability is said to be<

a. 6ositiveb. Fegativec. Feutral

1). Which of the following is wrong about stability?a. Static stability is the production of a restorative forceb. $ynamic stability refers to the oscillatory behaviourc. It is not possible to have statically stable system without

being dynamically stable

1+. Bnder the e#ect of a disturbance( an airplane

oscillates with divergent oscillations. What is the behavour

of airplane?

a. Statically and dynamically unstableb. Statically stable and dynamically unstablec. Statically and dynamically stable

1,. /t a turn in constant altitude with a ban! angle of 25

the load factor is about?a. ." gb. 1.) g

c. ".& g

1. Which statement is correct for gliding condition?a. The magnitude of the lift vector is e;ual to the wieght

vector but acts opposite to itb. The resultant of lift and drag acts opposite to the weight

vector and the same magnitude

c. The weight vector is greater than the lift and dragvector together. Therefore the aircraft descends.

7/17/2019 Module 8


11. When the %J approches to the %6 of the aircraft<a. Static stability will be increasedb. The aircraft losts its controlc. The stability becomes neutral

111. 0olling bac! of an aircraft without any e#ect of pilot

after a disturbance is called<a. $irectional stabilityb. 4ateral stabilityc. 4ongitudinal stability

112. Which of the following wing con-guration improves

the directional stability?a. / dihedral wingb. /n anhedral wingc. Swept bac! wings

113. What is the I%/ Standard atmospheric pressure

e'pressed in h6a K in Dg?a. 112.2& in h6a K 2,.2 in Dgb. 113.2& in h6a K 2.2 in Dgc. 131.1& in h6a K 22 in Dg

11". The partial pressure of nitrogen in dry atmosphere ata total air pressure of 1 h6a is <?a. 1 h6ab. 21 h6ac. +, h6a

11&. Which parameter according to IS/ is correct?a. The absolute temperature at an altitude of 1 ft is

about 2,) L

7/17/2019 Module 8


b. The relative humidity is 1 percent at mean sea levelc. The Standard air pressure measures 22 inches of

mercury

11). What is the temperature at an altitude of 2 !m

according to IS/?a. 12 5%b. 2 5%c. 11 5%

11+. Which statement about aerodynamic lift is correct?a. If the airspeed increases the lift decreasesb. If the surface area of an airfoil is increased also the lift

increasesc. The lift is inuenced by speed of sound

11,. Which statement about wing aspect ratio is correct?a. The induced drag doesnt depend on the aspect ratiob. The higher aspect ratio the less induced dragc. The higher aspect ratio the more induced drag

11. Which statement for IS/ is correct in the range from

11 !m to 2 !m altitude?

a. =oth temperature and pressure stay constantb. Temparature and pressure decreasec. Temperature stay constant while the pressure decreases

12. What happens when the %J approches the %6 of an

aircraft?a. Static stability will be increasedb. The aircraft will be out of control immediatelyc. The e;uilibrium acts more indi#erent

7/17/2019 Module 8


121. Ice formation on an airfoil generates<?a. / higher stall speedb. / lower stall speedc. 0educed drag

122. What happens to dynamic pressure when static

pressure increases?a. $ecreases proportionallyb. Increases proportionallyc. Stays stable

123. Which statement is true?a. Troposhere contains +& percent of total mass of air but

this is only 1 percent of the volume of the atmosphere

b. Deight of troposhere is the same from all places of earthc. The tropopause contains at least & percent of the total

mass of the atmosphere

12". Which vector change occurs when an aircraft has a

coordinated turn?a. The coeEcient of drag decreasesb. The resultant lift of the aircraft decreasesc. The resultant weight of the aircraft increases

12&. What does lift coeEcientM%lN depend on?a. /irfoil shape and angle of attac!b. /irspeed and air pressure

c. Surface area of the wing and density

7/17/2019 Module 8


19/ 2)9= &19/ +)9% 119=29% 2+9= &29% ++9/ 129/39/ 2,9/ &39= +,9/ 139%"9= 29/ &"9= +9% 1"9/&9= 39= &&9% ,9/ 1&9%)9/ 319/ &)9= ,19% 1)9%+9/ 329% &+9/ ,29% 1+9=,9= 339/ &,9= ,39= 1,9=9/ 3"9= &9= ,"9% 19=19= 3&9/ )9= ,&9% 119%119/ 3)9% )19% ,)9/ 1119=129% 3+9= )29/ ,+9/ 1129%139= 3,9% )39% ,,9/ 1139=1"9= 39/ )"9= ,9/ 11"9%1&9/ "9% )&9= 9% 11&9/1)9% "19= ))9/ 19/ 11)9=1+9% "29% )+9/ 29= 11+9=1,9= "39/ ),9= 39% 11,9=19/ ""9/ )9= "9% 119%29% "&9% +9% &9/ 129%219= ")9= +19% )9% 1219/229% "+9= +29/ +9= 1229/239= ",9% +39% ,9/ 1239/2"9% "9= +"9/ 9= 12"9%2&9/ &9= +&9= 19% 12&9/

TEST – 1

1. What is the partial pressure of o'ygen at an altitude with an atmospheric

pressure of & h6a?a. 3 h6a

7/17/2019 Module 8


b. 21 h6ac. 1& h6a

2. What does C1* relative humidity> mean?

a. It indicates that the air is perfectly dryb. It means that the air has absorbed all water it is able to doc. It shows the air contains no water at all and it is relatively denser

3. The air temperature at an altitude of 3. feet is <a. 9"&5%b. 9&).&5%c. O35L

". Which of the followings is not correct for atmospheric pressure?a. /s we go higher( air pressure becomes lessb. /tmospheric pressure varies also with temperature( density and

humidityc. /tmospheric pressure is the volume of air over a given area

&. When the relative humidity increases( the density of a#ected air mass <a. $ecreases

b. Increasesc. Stays stable

). /n increase in the velocity of air will cause the potential energy of the air

to be <a. %onstantb. Increasesc. $ecreased

+. What can be said for total pressure of a gas when the velocity of the gas is

doubled?a. It is doubledb. It is four times more than beforec. It stays stable

,. Which of the following causes s!in friction drag?a. The airow passing over the aircraft and tends to stic! to the s!inb. The air owing over one portion of the airframe interfering with the

smooth ow of air over another portionc. 6ressure di#erences between upper and lower surfaces

7/17/2019 Module 8


. Wave drag is the drag caused by<a. Wing tip vorticesb. ibrations generated by enginec. Jeneration of shoc! waves

1.What is the relation between lift coeEcient and angle of attac!?a. /s the angle of attac! increases( lift coeEcient increases proportionallyb. /s the angle of attac! increases( lift coeEcient increases up to a point

and then starts to decrease dramaticallyc. /s the angle of attac! increases( -rstly it decreases and then it start to

increase continously

11.Which condition should be provided to !eep an aircraft at a constant

velocity?a. 4ift must e;ual to weightb. Pngine should have some reserve of power enough to accelerate the

aircraftc. DoriGontally bac!ward forces must e;ual horiGontally forward forces

12./n aircraft with a lide ration of 12 descends from 2. feet to 1.+

feet. What is the horiGontal distance ta!en?a. 1& feetb. ). feetc. 3". feet

13.What is the load factor on an aircraft during a level ight?a. 1 gb. gc. 91 g

1".What is the e#ect of a higher load factor at constant altitude in comparison

with level ight?a. Increases stall speedb. $ecreases stall speedc. Fo e#ect on stall speed

1&.Which of the following about lift augmentation devices is correct?a. %amber of the wing surface may only be increased by deecting the

trailing edgeb. Slats allow a higher // before stall

7/17/2019 Module 8


c. / wing may have either a slot or ap

1).Which surface can be used to change the position of an aircraft around

vertical a'is?a. 0udderb. DoriGontal stabiliserc. Plevator

1+.In relation to which a'is is an aircraft>s longitudinal stability e'pressed?

a. ertical a'isb. 4ateral a'isc. 4ongitudinal a'is

1,.Which other name can be given to the stability in roll?a. 4ongitudinal stabilityb. $irectional stabilityc. 4ateral stability

1.Which type of wing may assist an aircraft to yaw bac! to the former

position after a disturbance?a. Sweepbac! wingb. $ihedral wingc. Sawtooth wing

2.Which can be said for the stabilities of an aircraft that has an undamped

oscillation behaviour?a. Statically stable and dynamically unstable

b. Statically stable and dynamically neutralc. Statically unstable and dynamically stable

7/17/2019 Module 8


1.c – 2.b – 3.a – 4.c – 5.a – 6.c – 7.c – 8.a – 9.c – 10.b – 11.c – 12.b – 13.a – 14.a –

15.b – 16.a – 17.b – 18.c – 19.a – 20.b

Test – 2

1. Which is not correct for standard atmospheric temperature?a. It remains constant at 9&).&5 from S4 to an altitude of 2 !mb. /ir temperature at S4 is O1&5%c. /ir temperature at an altitude of 2. feet is 115%

2. Which type of drag can not be classi-ed as pro-le drag?a. Interference dragb. Aorm drag

c. Induced drag

3. The line where the airow seperates so that some of it can pass over the

top and rest along the mottom of wing is called <a. %hord lineb. Stagnatin linec. ean camber line

". Aor a rectangular wing( wing span is , times longer than the length ofchord. What is the value of wing aspect ratio?a. 17,b. ,c. :

&. What is the name of line on a wing where all aerodynamic and

gravitational forces are located?a. ean camber lineb. Stagnation linec. ean aerodynamic chord

). Which of the following can be a correct de-nition of the term Cwash out>?a. Wash out is a twist that decreases the angle of incidence near the wing

rootb. Wash out is a twist that decreases the angle of incidence near the wing

tipc. Wash out is a twist that increases the angle of incidence near the wing

tip

7/17/2019 Module 8


+. Which of the following can ma!e a change in drag coeEcient?a. %hanging the power settings

b. Alying at an altitude relatively denserc. P'tending the leading edge aps

,. Which parameter is not common in lift and drag e;uations?a. elocityb. Surface areac. %oeEcient

. Dow can a best glide angle be found for an aircraft?a. =y use of a tangent from the Gero point in polar diagramb. =y -nding the angle at which highest lift coeEcient is obtainedc. =y -nding the angle at which lowest drag coeEcient is obtained

1.Dow does the airspeed inuence icing on planes?a. The higher air speed the higher ice build upb. The higher air speed the less ice build upc. Fo e#ect since it doesnt ma!e any change in temperature

11.Which of the icing factors doesnt inuence the type of ice formation?a. Temperatureb. $roplet siGec. /irfoil siGe

12.Which one is incorrect for drag?a. 6arasite drag increases as the airspeed increases

b. Induced drag increases as the airspeed increasesc. The total drag is least where induced and parasite drags are e;ual

13.What is the value of gliding angle if $74 e;uals 1 during gliding?a. 1&5b. 35c. "&5

1".Which of the following structures is an aid to minimiGe adverse yaw?a. Slots

7/17/2019 Module 8


b. Alapsc. Arise ailerons

1&.Which of the following is not correct for load factor?

a. 4oad factor can not be less than 1 gb. When the lift is smaller than weight that creates a negative load factorc. $uring a stall a load factor can be reduced towards Gero

1)./round which a'is is directional stability achieved?a. 4ongitudinal a'isb. ertical a'isc. 4ateral a'is

1+.Which wing design is used to prevent spanwise ow and seperations on an

airow in highly sweepbac! wings?a. 4eading edge apsb. Sawtooth leading edgec. Slats

1,.Which is wrong about stability?a. /n aircraft will dynamically be stable if it returns to ots original steady

ight attitudeb. /n aircraft will statically be stable if it returns to the state of static

e;uilibriumc. $ynamic stability is an essential prere;uisite for static stability

1.When the %J move away from %6<a. $ynamic stability will be increasedb. It will be statically stablec. P;uilibrium will be more di#erent

2.Which option creates a nose down moment?a. Thrust is @ust below the %Jb. $rag is above the %Jc. %J>s position ahead of the center of lift

1.a 9 2.c 9 3.b 9 ".a 9 &.c 9 ).b 9 +.c 9 ,.c 9 .a 9 1.b 9 11.c 9 12.b 9 13.c 9 1".c 9 1&.a

9 1).b 9 1+.b 9 1,.c 9 1.c 9 2.c

Documents

Module 8