Module 8 Exam 1 Module 8 Exam 1 Aerodynamics Aerodynamics
1.
1. On a swept wiOn a swept wing aircraft if both wng aircraft if both wing tip sections ling tip sections lose lift simultaneously tose lift simultaneously the aircraft wilhe aircraft willl a) roll
a) roll
b) pitch nose up b) pitch nose up c) pitch nose down c) pitch nose down
2.
2. ift ift on a on a delta delta wing wing aircraftaircraft
a) increases with an increased angle of incidence !angle of attac") a) increases with an increased angle of incidence !angle of attac") b) decreases with an increase in angle of incidence !angle of attac") b) decreases with an increase in angle of incidence !angle of attac") c) does not change with a change in angle of incidence !angle of attac") c) does not change with a change in angle of incidence !angle of attac")
#.
#. On a stOn a straight wraight wing aircraft$ ing aircraft$ stall commences stall commences at theat the a) root on a high
a) root on a high thic"ness ratio wingthic"ness ratio wing b) tip on a high thic"ness
b) tip on a high thic"ness ratio wingratio wing c) tip on a low thic"ness ratio wing c) tip on a low thic"ness ratio wing
%.
%. On a On a high whigh wing ing aircraft aircraft in a in a turnturn
a) the up&going wing loses lift causing a de
a) the up&going wing loses lift causing a de &stabilising effect&stabilising effect b) the down&going wing gains lift causing a stabilising effect b) the down&going wing gains lift causing a stabilising effect c) the down&going wing loses lift causing a de&stabilising effect c) the down&going wing loses lift causing a de&stabilising effect
'.
'. (or the (or the same angle same angle of attac"$ of attac"$ the lift the lift on a delton a delta winga wing a) is greater than the lift on
a) is greater than the lift on a high aspect ratio winga high aspect ratio wing b) is lower than the lift on a
b) is lower than the lift on a high aspect ratio winghigh aspect ratio wing c) is the same as the lift on a high aspect ratio wing c) is the same as the lift on a high aspect ratio wing
.
. *he *he +,A+,A
a) is ta"en from the e-uator a) is ta"en from the e-uator
b) is ta"en from %' degrees latitude b) is ta"en from %' degrees latitude c) assumes a standard day
c) assumes a standard day
.
. At At higher higher altitudes altitudes as as altitude altitude increases$ increases$ pressurepressure a) decreases at constant rate
a) decreases at constant rate b) increases exponentially b) increases exponentially c) decreases exponentially c) decreases exponentially
8.
8. *he thrust&drag coupl*he thrust&drag couple o/ercomes the lie o/ercomes the lift&weight couple. ft&weight couple. 0hat direction of f0hat direction of force is re-uired to be orce is re-uired to be producedproduced by the tail of the
by the tail of the aircraft to maintain straight and le/el flightaircraft to maintain straight and le/el flight a) upwards a) upwards b) downwards b) downwards c) sideways c) sideways .
. 0hen the pressure is 0hen the pressure is half of that half of that at sea lat sea le/el$ we/el$ what is hat is the altitudethe altitude a) 12$333 ft a) 12$333 ft b) 8$333 ft b) 8$333 ft c) 18$333 ft c) 18$333 ft 13.
13. 4uring a 4uring a turn$ the turn$ the stalling stalling angleangle a) increases
a) increases b) decreases b) decreases
c) remains the same c) remains the same Module 8 Exam 2
Module 8 Exam # Module 8 Exam # Aerodynamics Aerodynamics
1.
1. At At stall$ stall$ the wthe wingtip ingtip stagnation stagnation pointpoint
a) mo/es toward the lower surface of the a) mo/es toward the lower surface of the wingwing b) mo/es toward the upper surface of
b) mo/es toward the upper surface of the wingthe wing c) doesn9t mo/e
c) doesn9t mo/e
2.
2. :ow does :ow does +A, at +A, at the point the point of stall of stall /ary w/ary with heightith height a) +t is practically constant a) +t is practically constant b) +t increases b) +t increases c) +t decreases c) +t decreases #.
#. *he rigg*he rigging angle ing angle of incidence of incidence of an of an ele/ator iele/ator iss a) the angle between the mean
a) the angle between the mean chord line and the hori;ontal in the chord line and the hori;ontal in the rigging positionrigging position b) the angle between the bottom
b) the angle between the bottom surface of the ele/ator and surface of the ele/ator and the hori;ontal in the rigging positionthe hori;ontal in the rigging position c) the angle between the bottom surface of the ele/ator and the longitudinal datum
c) the angle between the bottom surface of the ele/ator and the longitudinal datum
%.
%. 0hat is 0hat is the lapse the lapse rate rate with with regard tregard to temperaturo temperaturee a) 1.8
a) 1.8oo6 per 1333 ft6 per 1333 ft b) 1.8
b) 1.8oo( per 1333 ft( per 1333 ft c) %
c) %oo6 per 1333 ft6 per 1333 ft
'.
'. 0hat happens t0hat happens to load o load factor factor as you as you decrease turn decrease turn radiusradius a) +t increases a) +t increases b) +t decreases b) +t decreases c) +t remains constant c) +t remains constant .
. +f you +f you steepen the asteepen the angle of a ngle of a ban"ed turn ban"ed turn without incwithout increasing airspeed reasing airspeed or angle of attac"$ or angle of attac"$ what wiwhat will thell the aircraft do
aircraft do
a) +t will remain at the same height a) +t will remain at the same height
b) +t will sideslip with attendant loss of height b) +t will sideslip with attendant loss of height c) +t will stall
c) +t will stall
.
. An aircrAn aircraft wiaft wing tends to ng tends to stall stall first atfirst at a) the tip due to
a) the tip due to a higher ratio thic"ness<chorda higher ratio thic"ness<chord b) the tip due to
b) the tip due to a lower ratio thic"ness<chorda lower ratio thic"ness<chord c) the root due to
c) the root due to a higher ratio thic"ness<chorda higher ratio thic"ness<chord
8.
8. 4ihedral 4ihedral wings wings combat combat instability instability inin a) pitch a) pitch b) yaw b) yaw c) sideslip c) sideslip .
. *o stop ai*o stop aircraft decreasing rcraft decreasing in height in height during a during a sideslip$ tsideslip$ the pilot he pilot cancan a) ad/ance the throttle
a) ad/ance the throttle
b) pull bac" on the control column b) pull bac" on the control column c) ad=ust the rudder position c) ad=ust the rudder position
13.
13. 0hat control surface mo/ements 0hat control surface mo/ements will will ma"e an aircraft ma"e an aircraft fitted with fitted with rudder/ators yaw rudder/ators yaw to the leftto the left a) eft rudder/ator lowered$ right rudder/ator raised
a) eft rudder/ator lowered$ right rudder/ator raised b) >ight rudder/ator lowered$ left rudder/ator raised b) >ight rudder/ator lowered$ left rudder/ator raised c) ?oth rudder/ators raised
Module 8 Exam # Module 8 Exam # Aerodynamics Aerodynamics
1.
1. At At stall$ stall$ the wthe wingtip ingtip stagnation stagnation pointpoint
a) mo/es toward the lower surface of the a) mo/es toward the lower surface of the wingwing b) mo/es toward the upper surface of
b) mo/es toward the upper surface of the wingthe wing c) doesn9t mo/e
c) doesn9t mo/e
2.
2. :ow does :ow does +A, at +A, at the point the point of stall of stall /ary w/ary with heightith height a) +t is practically constant a) +t is practically constant b) +t increases b) +t increases c) +t decreases c) +t decreases #.
#. *he rigg*he rigging angle ing angle of incidence of incidence of an of an ele/ator iele/ator iss a) the angle between the mean
a) the angle between the mean chord line and the hori;ontal in the chord line and the hori;ontal in the rigging positionrigging position b) the angle between the bottom
b) the angle between the bottom surface of the ele/ator and surface of the ele/ator and the hori;ontal in the rigging positionthe hori;ontal in the rigging position c) the angle between the bottom surface of the ele/ator and the longitudinal datum
c) the angle between the bottom surface of the ele/ator and the longitudinal datum
%.
%. 0hat is 0hat is the lapse the lapse rate rate with with regard tregard to temperaturo temperaturee a) 1.8
a) 1.8oo6 per 1333 ft6 per 1333 ft b) 1.8
b) 1.8oo( per 1333 ft( per 1333 ft c) %
c) %oo6 per 1333 ft6 per 1333 ft
'.
'. 0hat happens t0hat happens to load o load factor factor as you as you decrease turn decrease turn radiusradius a) +t increases a) +t increases b) +t decreases b) +t decreases c) +t remains constant c) +t remains constant .
. +f you +f you steepen the asteepen the angle of a ngle of a ban"ed turn ban"ed turn without incwithout increasing airspeed reasing airspeed or angle of attac"$ or angle of attac"$ what wiwhat will thell the aircraft do
aircraft do
a) +t will remain at the same height a) +t will remain at the same height
b) +t will sideslip with attendant loss of height b) +t will sideslip with attendant loss of height c) +t will stall
c) +t will stall
.
. An aircrAn aircraft wiaft wing tends to ng tends to stall stall first atfirst at a) the tip due to
a) the tip due to a higher ratio thic"ness<chorda higher ratio thic"ness<chord b) the tip due to
b) the tip due to a lower ratio thic"ness<chorda lower ratio thic"ness<chord c) the root due to
c) the root due to a higher ratio thic"ness<chorda higher ratio thic"ness<chord
8.
8. 4ihedral 4ihedral wings wings combat combat instability instability inin a) pitch a) pitch b) yaw b) yaw c) sideslip c) sideslip .
. *o stop ai*o stop aircraft decreasing rcraft decreasing in height in height during a during a sideslip$ tsideslip$ the pilot he pilot cancan a) ad/ance the throttle
a) ad/ance the throttle
b) pull bac" on the control column b) pull bac" on the control column c) ad=ust the rudder position c) ad=ust the rudder position
13.
13. 0hat control surface mo/ements 0hat control surface mo/ements will will ma"e an aircraft ma"e an aircraft fitted with fitted with rudder/ators yaw rudder/ators yaw to the leftto the left a) eft rudder/ator lowered$ right rudder/ator raised
a) eft rudder/ator lowered$ right rudder/ator raised b) >ight rudder/ator lowered$ left rudder/ator raised b) >ight rudder/ator lowered$ left rudder/ator raised c) ?oth rudder/ators raised
Module 8 Exam % Module 8 Exam % Aerodynamics Aerodynamics
1.
1. 0hen a leading edge 0hen a leading edge slat opens$ slat opens$ there is there is a gap betwa gap between the sleen the slat and the at and the wing. wing. *his is*his is a) to allow it to retract bac" into the wing
a) to allow it to retract bac" into the wing
b) to allow air through to re&energi;e the bounda
b) to allow air through to re&energi;e the bounda ry layer on top of the ry layer on top of the wingwing c) to "eep the area of the wing the same
c) to "eep the area of the wing the same
2.
2. 0hich of 0hich of the the following following is is truetrue
a) ift acts at right angles to the
a) ift acts at right angles to the wing chord line and weight acts /ertically downwing chord line and weight acts /ertically down b) ift acts at right angles to the
b) ift acts at right angles to the relati/e airflow and weight acts /ertically dowrelati/e airflow and weight acts /ertically downn c) ift acts at right angles to the relati/e air
c) ift acts at right angles to the relati/e air flow and weight acts at right angles to the aircraft centrflow and weight acts at right angles to the aircraft centree line
line
#.
#. +f the wi+f the wing tips stall before ng tips stall before the root on a the root on a swept wiswept wing aircraft$ ng aircraft$ the aircraft wthe aircraft willill a) roll
a) roll
b) pitch nose up b) pitch nose up c) pitch nose down c) pitch nose down
%.
%. ift ift on a on a delta delta wing wing aircraftaircraft
a) increases with an increased angle of incidence !angle of attac") a) increases with an increased angle of incidence !angle of attac") b) decreases with an increase in angle of incidence !angle of attac") b) decreases with an increase in angle of incidence !angle of attac") c) does not change with a change in angle of incidence !angle of attac") c) does not change with a change in angle of incidence !angle of attac")
'.
'. On a On a straight straight wing wing aircraft$ aircraft$ stall stall commences at thecommences at the a) root on a high
a) root on a high thic"ness ratio wingthic"ness ratio wing b) tip on a high thic"ness
b) tip on a high thic"ness ratio wingratio wing c) tip on a low thic"ness ratio wing c) tip on a low thic"ness ratio wing
.
. On a On a high whigh wing ing aircraft aircraft in a in a turnturn
a) the up&going wing loses lift causing a d
a) the up&going wing loses lift causing a d e&stabili;ing effecte&stabili;ing effect b) the down&going wing gains lift causing a stabili;ing effect b) the down&going wing gains lift causing a stabili;ing effect c) the down&going wing loses lift causing a de&stabili;ing effect c) the down&going wing loses lift causing a de&stabili;ing effect
.
. (or the (or the same angle same angle of attac"$ of attac"$ the lift on a the lift on a delta widelta wingng a) is greater than the lift on
a) is greater than the lift on a high aspect ratio winga high aspect ratio wing b) is lower than the lift on a
b) is lower than the lift on a high aspect ratio winghigh aspect ratio wing c) is the same as the lift on a high aspect ratio wing c) is the same as the lift on a high aspect ratio wing
8.
8. ,tandard ,tandard sea lsea le/el e/el temperature temperature isis a) 3 degrees 6elsius a) 3 degrees 6elsius b) 1' degrees 6elsius b) 1' degrees 6elsius c) 23 degrees 6elsius c) 23 degrees 6elsius .
. As As altitude altitude increases$ increases$ pressurepressure a) decreases at constant rate a) decreases at constant rate b) increases exponentially b) increases exponentially c) decreases exponentially c) decreases exponentially
13.
13. 4eployment of 4eployment of a split a split flap wilflap willl
a) increase wing area and increase drag a) increase wing area and increase drag b) pitch the nose down and decrease drag b) pitch the nose down and decrease drag c) increase camber and increase drag c) increase camber and increase drag
Module 8 Exam ' Module 8 Exam ' Aerodynamics Aerodynamics
1.
1. apse apse rate rate usually usually refers refers toto a) 5ressure a) 5ressure b) 4ensity b) 4ensity c) *emperature c) *emperature 2.
2. 4uring 4uring a tura turn$ n$ the stthe stalling alling angleangle a) increases
a) increases b) decreases b) decreases
c) remains the same c) remains the same
#.
#. *he /erti*he /ertical fin cal fin of a of a single single engine aircraft engine aircraft isis
a) parallel with both the longitudinal axis and /ertical axis a) parallel with both the longitudinal axis and /ertical axis b) parallel with the longitudinal axis but not the
b) parallel with the longitudinal axis but not the /ertical axis/ertical axis c) parallel with the /ertical axis but not the longitudinal axis c) parallel with the /ertical axis but not the longitudinal axis
%.
%. Aircraft Aircraft flying flying in the in the transonic rtransonic range most ange most often utili;often utili;ee a) sweptbac" wings
a) sweptbac" wings
b) ad/anced supercritical airfoils b) ad/anced supercritical airfoils c) high wings
c) high wings
'.
'. 0hich type 0hich type of flap of flap changes the changes the area of area of the wthe winging a) (owler a) (owler b) ,plit b) ,plit c) ,lotted c) ,lotted .
. (orward swept (orward swept wings tend to stwings tend to stall at the root all at the root first so the first so the aircraft retains lateral contaircraft retains lateral control$ so why rol$ so why are theyare they ne/er used on passenger aircraft
ne/er used on passenger aircraft a) ?ecause the wing tips wash in at h
a) ?ecause the wing tips wash in at h igh wing loadsigh wing loads b) ?ecause the wing tips wash out at
b) ?ecause the wing tips wash out at high wing loadshigh wing loads
c) ?ecause at high loads their angle of incidence increases and the loads imposed on the wing can c) ?ecause at high loads their angle of incidence increases and the loads imposed on the wing can
increase until they destroy it increase until they destroy it
.
. 0hat happens to air 0hat happens to air flowing flowing at the speed at the speed of sound wof sound when it enters hen it enters a con/erging a con/erging ductduct a) @elocity decreases$ pressure and density increase
a) @elocity decreases$ pressure and density increase b) @elocity increases$ pressure and density decreases b) @elocity increases$ pressure and density decreases c) @elocity$ pressure and density increase
c) @elocity$ pressure and density increase
8.
8. As the angAs the angle of attacle of attac" of an " of an airfoil iairfoil increases the centrncreases the centre of pressuree of pressure a) mo/es forward a) mo/es forward b) mo/es aft b) mo/es aft c) remains stationary c) remains stationary .
. An aircraftAn aircraft$ which $ which is longitudinallis longitudinally stable$ y stable$ will will tend to rettend to return to lurn to le/el flight e/el flight after a after a mo/ement about mo/ement about which axiwhich axiss a) 5itch a) 5itch b) >oll b) >oll c) aw c) aw 13.
13. @apour trails from the w@apour trails from the wingtips of an aircraft in ingtips of an aircraft in flight are caused byflight are caused by a) low pressure abo/e the wing and high
a) low pressure abo/e the wing and high pressure below the wing causing /orticespressure below the wing causing /ortices b) high pressure abo/e the wing and
b) high pressure abo/e the wing and low pressure below the wing causing /orticeslow pressure below the wing causing /ortices c) low pressure abo/e the wing and high pressure
Module 8 Exam Aerodynamics
1. @ortex generators on the wing are most effecti/e at a) high speed
b) low speed
c) high angles of attac"
2. *he chord line of a wing is a line that runs from
a) the centre of the leading edge of the wing to the trailing edge b) half way between the upper and lower surface of the wing c) one wing tip to the other wing tip
#. *he angle of incidence of a wing is an angle formed by lines a) parallel to the chord line and longitudinal axis
b) parallel to the chord line and the lateral axis c) parallel to the chord line and the /ertical axis
%. *he centre of pressure of an aerofoil is located
a) #3 & %3B of the chord line bac" from the leading edge b) #3 & %3B of the chord line forward of the leading edge c) '3B of the chord line bac" from the leading edge
'. 6ompressibility effect is
a) drag associated with the form of an aircraft
b) drag associated with the friction of the air o/er the surface of the aircraft
c) the increase in total drag of an aerofoil in transonic flight due to the formation of shoc" wa/es
. ateral control of an aircraft at high angle of attac" can be maximised by using a) fences
b) /ortex generators c) wing slots
. ,tall strips are always a) made of metal
b) on the leading edge of a wing c) fitted forward of the ailerons
8. ,tall strips
a) cause the wing root to stall b) cause the wing tip to stall
c) cause the wings to stall symmetrically
. 4ue to the interference of the airflow on a high wing aircraft between the fuselage and the wings$ the lateral stability of the aircraft in a gusty wind situation will cause
a) the upper wing to increase its lift b) the upper wing to decrease its lift c) the lower wing to decrease its lift
13. ,lats
a) reduce the stall speed
b) reduce the tendency of the aircraft to aw c) decrease the aerofoil drag at high speeds
Module 8 Exam Aerodynamics
1. A high aspect ratio wing will gi/e
a) high profile and low induced drag b) low profile and high induced drag c) low profile and low induced drag
2. Aerofoil efficiency is defined by a) lift o/er drag
b) drag o/er lift c) lift o/er weight
#. An aircraft ban"s into a turn. o change is made to the airspeed or angle of attac". 0hat will happen a) *he aircraft enters a side slip and begins to lose altitude
b) *he aircraft turns with no loss of height c) *he aircraft yaws and slows down
%. *he relationship between induced drag and airspeed is$ induced drag is a) directly proportional to the s-uare of the speed
b) in/ersely proportional to the s-uare of the speed c) directly proportional to speed
'. 0hat is the definition of Angle of +ncidence
a) *he angle the underside of the mainplane or tailplane ma"es with the hori;ontal
b) *he angle the underside of the mainplane or tailplane ma"es with the longitudinal datum line c) *he angle the chord of the mainplane or tailplane ma"es with the hori;ontal
. 0hat is ?oundary ayer
a) ,eparated layer of air forming a boundary at the leading edge b) *urbulent air mo/ing from the leading edge to trailing edge
c) ,luggish low energy air that stic"s to the wing surface and gradually gets faster until it =oins the f ree stream flow of air
. *he normal axis of an aircraft passes through a) the centre of gra/ity
b) a point at the centre of the wings c) at the centre of pressure
8. On a high winged aircraft$ what effect will the fuselage ha/e on the up&going wing
a) *he up&going wing will ha/e a decrease in angle of attac" and therefore a decrease in lift b) *he down&going will ha/e a decrease in angle of attac" and therefore a decrease in lift c) *he up&going wing will ha/e an increase in angle of attac" and therefore a decrease in lift
. 0hat is the collecti/e term for the fin and rudder and other surfaces aft of the centre of gra/ity that helps directional stability
a) Effecti/e "eel surface b) Empennage
c) (uselage surfaces
13. *emperature abo/e #$333 feet will a) decrease exponentially b) remain constant
Module 8 Exam 8 Aerodynamics
1. A decrease in incidence toward the wing tip may be pro/ided to a) pre/ent ad/erse yaw in a turn
b) pre/ent spanwise flow in maneu/ers
c) retain lateral control effecti/eness at high angles of attac"
2. *he angle of attac" which gi/es the best <4 ratio a) decreases with a decrease in density b) in unaffected by density changes c) increases with a decrease in density
#. (or a gi/en aerofoil production lift$ where [Ref to attached diagram] 5 C pressure and @ C /elocityD
a) 51 is greater than 52$ and @1 is greater than @2 b) 51 is less than 52 and @1 is greater than @2 c) 51 is greater than 52$ and @1 is less than @2
%. ow wing loading
a) increases stalling speed$ landing speed and landing run b) increases lift$ stalling speed and maneu/erability
c) decreases stalling speed$ landing speed and landing run
'. 4ue to the change in downwash on an untapered wing !i.e. one of constant chord length) it will a) not pro/ide any damping effect when rolling
b) tend to stall first at the root
c) not suffer ad/erse yaw effects when turning
. *rue stalling speed of an aircraft increases with altitude
a) because reduced temperature causes compressibility effect b) because air density is reduced
c) because humidity is increased and this increases drag
. As a general rule$ if the aerodynamic angle of incidence !angle of attac") of an aerofoil is slightly increased$ the centre of pressure will
a) ne/er mo/e
b) mo/e forward towards the leading edge c) mo/e towards the tip
8. *he wing setting angle is commonly "nown as a) angle of incidence
b) angle of attac" c) angle of dihedral
. On a /ery humid day$ an aircraft ta"ing off would re-uire a) a shorter ta"e off run
b) a longer ta"e off run
c) humidity does not affect the ta"e off run
13. An aircraft is flying at #'3 M5:$ into a head wind of ' M5:$ what will its ground speed be a) 1' mph
b) 2' mph c) 233 mph
Module 8 Exam Aerodynamics
1. 0hen does the angle of incidence change a) 0hen the aircraft attitude changes
b) 0hen the aircraft is ascending or descending c) +t ne/er changes
2. As the angle of attac" decreases$ what happens to the centre of pressure a) +t mo/es forward
b) +t mo/es rearwards
c) 6entre of pressure is not affected by angle of attac" decrease
#. A decrease in pressure o/er the upper surface of a wing or aerofoil is responsible for a) approximately 2<# !two thirds) of the lift obtained
b) approximately 1<# !one third) of the lift obtained c) approximately 1<2 !one half) of the lift obtained
%. 0hich of the four forces act on an aircraft a) ift$ gra/ity$ thrust and drag
b) 0eight$ gra/ity$ thrust and drag c) ift$ weight$ gra/ity and drag
'. 0hich of the following types of drag increases as the aircraft gains altitude a) 5arasite drag
b) +nduced drag c) +nterference drag
. 6orrecting for a disturbance which has caused a rolling motion about the longitudinal axis would re&establish which of the following
a) ateral stability b) 4irectional stability c) ongitudinal stability
. *he layer of air o/er the surface of an aerofoil which is slower mo/ing$ in relation to the rest of the airflow$ is "nown as
a) camber layer b) boundary layer c) none of the abo/e
8. 0hat is a controlling factor of turbulence and s"in friction a) Aspect ratio
b) (ineness ratio
c) 6ounter sun" ri/ets used on s"in exterior
. 6hanges in aircraft weight
a) will not affect total drag since it is dependant only upon speed
b) cause corresponding changes in total drag due to the associated lift change c) will only affect total drag if the lift is "ept constant
13. *he aircraft stalling speed will
a) increase with an increase in weight
b) be unaffected by aircraft weight changes since it is dependant upon the angle of attac" c) only change if the M*MA were changed
Module 8 Exam 13 Aerodynamics
1. +n a ban" and turn
a) extra lift is not re-uired
b) extra lift is not re-uired if thrust is increased c) extra lift is re-uired
2. *o maintain straight and le/el flight on the aeroplane shown$ with a decrease in tail&plane download the mainplane lift would ha/e to [Ref to attached diagram]
a) remain constant b) decrease
c) increase
#. *o achie/e the maximum distance in a glide$ the recommended air speed is a) as close to the stall as practical
b) as high as possible with @E
c) the speed where the <4 ratio i s maximum
%. +f the 6 of 7 is aft of the 6entre of 5ressure
a) changes in lift produce a pitching moment which acts to increase the change in lift
b) when the aircraft sideslips$ the 6 of 7 causes the nose to turn into the sideslip thus applying a restoring moment
c) when the aircraft yaws the aerodynamic forces acting forward of the 6entre of 5ressure
'. 5orpoising is an oscillatory motion in the a) pitch plane
b) roll plane c) yaw plane
. 4irectional stability is maintained
a) by the mainplanes$ and controlled by the ailerons b) by the tailplane$ and controlled by the ele/ators
c) by the "eel surface and fin$ and controlled by the rudder
. 4ue to the interference effects of the fuselage$ when a high wing aeroplane sideslips a) the accompanying rolling due to "eel surface area is destabili;ing
b) the accompanying lift changes on the wings produces a stabili;ing effect c) the accompanying rolling due to the fin is destabili;ing
8. *he power re-uired in a hori;ontal turn
a) is greater than that for le/el flight at the same airspeed
b) must be the same as that for le/el flight at the same airspeed c) is less than that for le/el flight at the same airspeed
. A wing mounted stall sensing de/ice is located a) usually on the under surface
b) always at the wing tip c) always on the top surface
13. (or an aircraft in a glide
a) thrust$ drag$ lift and weight act on the aircraft b) weight$ lift and drag act on the aircraft
Module 8 Exam 11 Aerodynamics
1. *he upper part of the wing in comparison to the lower a) de/elops more lift
b) de/elops the same lift c) de/elops less lift
2. 0hat effect would a forward 67 ha/e on an aircraft on landing a) +ncrease stalling speed
b) o effect on landing c) >educe stalling speed
#. F: refers to
a) -uite near hori;on
b) setting the altimeter to ;ero
c) setting the mean sea le/el atmospheric pressure so an altimeter reads the aerodrome altitude abo/e mean sea le/el
%. FE refers to
a) ,etting an altimeter to read aerodrome a ltitude abo/e sea le/el b) -uite new e-uipment
c) setting the mean sea le/el a tmospheric pressure in accordance with +6AO standard atmosphere i.e. 131# millibars
'. An aspect ratio of 8 would mean a) span %$ mean chord 8 b) mean chord % $ span 8 c) span s-uared % $chord 8
. +f an aircraft in le/el flight loses engine power it will a) pitch nose up
b) pitch nose down
c) not change pitch without drag increasing
. F(E is
a) sea le/el pressure b) airfield pressure
c) difference between sea le/el and airfield pressure
8. *he lift <drag ratio at stall a) increases
b) decreases c) is unchanged
. On a straight unswept wing$ stall occurs at a) the thic" portion$ at the wing root b) the thic" portion$ at the wing tip c) the thin portion$ at the wing tip
13. 4uring a climb from a di/e
a) the thrust re-uired is greater than re-uired for le/el flight b) the thrust re-uired is lower than for le/el flight
Module 8 Exam 12 Aerodynamics
1. 0hen power is off$ the aircraft will pitch a) nose down
b) nose up c) trim le/el
2. Angle of attac" on a down going wing in a roll a) increases
b) decreases c) unaffected
#. (or any gi/en speed$ a decrease in aircraft weight$ the induced drag will a) increase
b) decrease
c) remain the same
%. *he amount of lift generated by a wing is a) greatest at the root
b) greatest at the tip
c) constant along the span
'. +nduced 4rag is
a) greatest towards the wing root and downwash is greatest at the tip b) greatest towards the wing tip and downwash is greatest towards the root c) greatest towards the tip and downwash decreases from tip to root
. +nduced 4rag is
a) e-ual to profile drag at stalling angle b) e-ual to profile drag at @md
c) ne/er e-ual to profile drag
. 0ith an increase in aircraft weight a) @md will be at the same speed b) @md will be at a lower speed c) @md will be at a higher speed
8. (or a gi/en +A, an increase in altitude will result in a) no change in the /alue of induced drag b) an increase in induced drag
c) an increase in profile drag
. As the angle of attac" of a wing is increased in le/el flight a) the 6of 7 mo/es aft and the 6of 5 forward
b) the 6of 5 and transition point mo/e forward
c) the 6of 5 mo/es forward and the stagnation point aft o/er the upper surface
13. ,tall inducers may be fitted to a wing
a) at the tip to cause the root to stall first b) at the root to cause the tip to stall first c) at the root to cause the root to stall first
Module 8 Exam 1# Aerodynamics
1. 0ith increasing altitude pressure decreases and
a) temperature decreases at the same rate as pressure reduces b) temperature decreases but at a lower rate than pressure reduces c) temperature remains constant to 8333 ft
2. 0hen deployed a Grueger (lap
a) increases the leading edge camber
b) allows high pressure air from beneath the wing to flow to the top c) energi;es the air flowing o/er the ailerons
#. 0hich conditions will gi/e the shortest ta"e off distance a) :ot :umid day at high ele/ation
b) 6old winter day at sea le/el c) :ot summer day at sea le/el
%. *he optimum angle of attac" of an aerofoil is the angle at which a) the aerofoil produces maximum lift
b) the aerofoil produces ;ero lift
c) the highest lift<drag ratio is produced
'. A high aspect ratio wing has a a) increased induced drag b) decreased induced drag c) decreased s"in friction drag
. Minimum total drag of an aircraft occurs a) at the stalling speed
b) when profile drag e-uals induced drag c) when induced drag is least
. +f the weight of an aircraft is increased$ the induced drag at a gi/en speed a) will increase
b) will decrease
c) will remain the same
8. *he transition point on a wing is the point where a) the flow separates from the wing surface
b) the boundary layer flow changes from laminar to turbulent c) the flow di/ides to pass abo/e and below the wing
. *he boundary layer of a body in a mo/ing airstream is
a) a thin layer of air o/er the surface where the air is stationary b) a layer of separated f low where the air is turbulent
c) a layer of air o/er the surface where the airspeed is changing from free stream speed to ;ero speed
13. A laminar boundary layer will produce
a) more s"in friction drag than a turbulent one b) less s"in friction drag than a turbulent one c) the same s"in friction drag as a turbulent one
Module 8 Exam 1% Aerodynamics
1. ongitudinal stability is gi/en by a) the fin
b) the wing dihedral c) the hori;ontal tailplane
2. ateral stability is gi/en by a) the ailerons
b) the wing dihedral c) the hori;ontal tailplane
#. ,tability about the lateral axis is gi/en by a) wing dihedral
b) the hori;ontal tailplane c) the ailerons
%. ,weepbac" of the wings will a) increase lateral stability b) decrease lateral stability c) not affect the lateral stability
'. 4utch >oll is
a) a combined rolling and yawing motion b) a type of slow roll
c) primarily a pitching instability
. A high wing position gi/es
a) more lateral stability than a low wing b) less lateral stability than a low wing c) the same lateral stability as a low wing
. On an aircraft in an unpowered steady speed descent a) the lift e-uals the weight
b) the weight e-uals the drag
c) the weight e-uals the resultant of the lift and drag
8. 0hen an aircraft rolls to enter a turn and power is not increased a) the lift e-uals the weight
b) the lift is greater than the weight c) the lift is less than the weight
. *he boundary layer is
a) thic"est at the leading edge b) thic"est at the trailing edge
c) constant thic"ness from leading to trailing edges
13. *he amount of thrust produced by a =et engine or a propeller can be calculated using a) ewton9s 1st law
b) ewton9s 2nd law c) ewton9s #rd law
Module 8 Exam 1' Aerodynamics
1. An engine which produces an efflux of high speed will be a) more efficient
b) less efficient
c) speed of efflux has no affect on the engine efficiency
2. 0hen an aircraft with a 6of 7 forward of the 6of 5 rolls$ the nose of the aircraft will a) stay le/el
b) rise c) drop
#. 4irectional stability may be increased with a) pitch dampers
b) horn balance c) yaw dampers
%. ateral stability may be increased with a) increased lateral dihedral b) increased lateral anhedral c) increased longitudinal dihedral
'. ongitudinal stability is increased if the a) 65 mo/es forward of the 67
b) *hrust acts on a line below the total drag c) 67 is forward of the 65
. 0ing loading is calculated by weight a) di/ided by gross wing area b) di/ided by lift
c) multiplied by gross wing area
. +nduced drag is
a) in/ersely proportional to the s-uare of speed b) proportional to speed
c) nothing to do with speed
8. +n a ban"$ the weight is a) increased b) decreased c) the same
. <4 ratio is
a) higher at supersonic cruise speed b) higher at sub sonic speed
c) the same
13. *he power re-uired at low altitude for a gi/en +A, is a) the same as at high altitude
b) higher c) lower
Module 8 Exam 1 Aerodynamics
1. +f the stall speed is ' "nots. 0hat is the same stall speed in mph a) ' x 3.8
b) ' < 3.8
c) ' < 3.8 x relati/e density
2. As the angle of attac" increases the stagnation point a) mo/es towards the upper surface
b) mo/es towards the lower surface c) does not mo/e
#. *he term pitch&up is due to a) compressibility effect b) ground effect
c) longitudinal instability
%. +n a steady climb at a steady +A,$ the *A, is a) more than +A,
b) less than +A, c) the same
'. An untapered straight wing will
a) ha/e no yaw effect in ban"ing
b) ha/e no change in induced drag in the ban" c) stall at the root first
. 0ith the ailerons away from the neutral$ induced drag is a) unchanged but profile drag is higher
b) higher on the lower wing plus profile drag increases c) higher on the upper wing plus profile d rag increases
. *he lift<drag ratio is
a) higher at mach numbers abo/e supersonic b) higher at sub sonic mach numbers
c) the same
8. *he force opposing thrust is a) drag
b) lift c) 0eight
. 4irectional stability is about the a) normal axis
b) longitudinal axis c) lateral axis
13. ateral stability is about the a) longitudinal axis b) normal axis c) /ertical axis
Module 8 Exam 1 Aerodynamics
1. All the lift can be said to act through the a) centre of pressure
b) centre of gra/ity c) normal axis
2. ongitudinal stability is pro/ided by the a) hori;ontal stabili;er
b) /ertical stabili;er c) mainplane
#. *he concept of thrust is explained by a) ewton9s 1st law
b) ewton9s #rd law c) ?ernoulli9s theorem
%. *he camber of an aerofoil section is
a) the cur/ature of the median line of the aerofoil b) the angle of incidence towards the tip of a wing
c) the angle which the aerofoil ma"es with the relati/e airflow
'. +f the aircraft turns and side&slips
a) the sweepbac" of the wing will correct the sideslip b) the dihedral of the wing will correct the sideslip c) the "eel surface will correct the sideslip
. Mo/ement of an aircraft about its lateral axis a) is pitching
b) is rolling c) is yawing
. +nduced drag
a) is caused by s"in friction
b) results from disturbed airflow in the region of mainplane attachments c) is associated with the lift generated by an aerofoil
8. 0hat is the temperature in comparison to +,A conditions at #3$333ft a) & 36
b) & '6 c) & %'6
. At what altitude is the tropopause a) #$333 ft.
b) #$333 ft. c) '$333 ft.
13. 0hat approximate percentage of oxygen is in the atmosphere a) 12B
b) 21B c) 8B
Module 8 Exam 18 Aerodynamics
1. 0hich has the greater density a) Air at low altitude
b) Air at high altitude c) +t remains constant
2. As air flows o/er the upper cambered surface of an aerofoil$ what happens to /elocity and pressure a) @elocity decreases$ pressure decreases
b) @elocity increases$ pressure increases c) @elocity increases$ pressure decreases
#. 0hat is the force that tends to pull an aircraft down towards the earth a) 4rag
b) *hrust c) 0eight
%. 0hich of the following act in opposition to forward mo/ement a) ift
b) 7ra/ity c) 4rag
'. *he angle at which the chord line of the aerofoil is presented to the airflow is "nown as a) angle of attac"
b) angle of incidence c) resultant
. *he imaginary straight line which passes through an aerofoil section from leading edge to trailing edge is called
a) centre of pressure
b) the direction of relati/e airflow c) the chord line
. 0hat is the angle between the chord line of the wing$ and the longitudinal axis of the aircraft$ "nown as a) angle of attac"
b) angle of incidence c) angle of dihedral
8. An aircraft disturbed from its normal flight path$ and automatically returns to that normal flight path$ without any action on the part of the pilot is "nown as
a) aircraft stability b) aircraft instability c) aircraft stall
. 4irectional control is pro/ided by a) hori;ontal stabili;er b) rudder
c) ele/ator
13. About which axis of the aircraft does a rolling motion ta"e place a) ormal axis
b) ongitudinal axis c) ateral axis
Module 8 Exam 1 Aerodynamics
1. 0hich motion happens about the lateral axis a) 5itching
b) awing c) >olling
2. 0ing tip /ortices create a type of drag "nown as a) form drag
b) induced drag c) profile drag
#. 0hich of the following describes the HEmpennageI a) ose section of an aircraft$ including the coc"pit
b) *ail section of the aircraft$ including fin$ rudder$ tail plane an d ele/ators c) *he wings$ including the ailerons
%. At what altitude does stratosphere commence approximately a) ,ea le/el
b) #$333 ft c) #$333 ft
'. 0hen an aircraft is in straight and le/el unaccelerated flight$ which of the following is correct a) ift and weight are e-ual$ and thrust and drag are e-ual
b) ift greater than weight$ and thrust greater than drag c) ift greater than weight$ and thrust is less than drag
. As the angle of attac" is increased !up to the stall point)$ which of the following is correct a) 5ressure difference between top and bottom of the wing increases
b) ift increases
c) ?oth a) and b) are correct
. *he fin gi/es stability about which axis a) ateral axis
b) ormal axis c) ongitudinal axis
8. 0hat is the hori;ontal mo/ement of the nose of the aircraft called a) >olling mo/ement
b) 5itching mo/ement c) awing mo/ement
. 0hat type of drag$ depends on the smoothness of the body$ and surface area o/er which the air flows a) 5arasite drag
b) (orm drag
c) ,"in friction drag
13. +f the nose of the aircraft is rotated about its lateral axis$ what is its directional mo/ement a) *urning to the left or right
b) >olling or ban"ing to the left or right c) 6limbing or di/ing
Module 8 Exam 23 Aerodynamics
1. 0hen air flow /elocity o/er an upper cambered surface of an aerofoil decreases$ what ta"es place a) 5ressure increases$ lift decreases
b) 5ressure increases$ lift increases c) 5ressure decreases$ lift increases
2. 0hen an aircraft stalls a) lift and drag increase
b) lift increases and drag decreases c) lift decreases and drag increases
#. 0ing loading is
a) the maximum all up weight multiplied by the total wing area b) the maximum all up weight di/ided by the total wing area c) the ratio of the all u p weight of the aircraft to its basic weight
%. An aircraft wing with an aspect ration of D1 is proportional so that a) the mean chord is six times the thic"ness
b) the wing span is six times the mean chord c) the wing area is six times the span
'. Jpward and outward inclination of a mainplane is termed a) sweep
b) dihedral c) stagger
. *he function of an aircraft fin
a) is to pro/ide stability about the normal axis b) is to pro/ide directional control
c) is to pro/ide straight airflow across the rudder
. Mo/ement of an aircraft about its normal axis a) is pitching
b) is rolling c) is yawing
8. A pressure of one atmosphere is e-ual to a) 1%. psi
b) 133 millibar c) 1 inch :g.
. *he millibar is a unit of
a) atmospheric temperature b) pressure altitude
c) barometric pressure
13. 0ith an increase in altitude under +.,.A. conditions the temperature in the troposphere a) increases
b) decreases
Module 8 Exam 21 Aerodynamics
1. 0hich of the following forces act on an aircraft in le/el flight a) ift$ thrust$ and weight
b) ift$ thrust$ weight$ and drag c) ift$ drag$ thrust
2. 0hen an aircraft is ban"ed$ the hori;ontal component of the lift a) will tend to ma"e the aircraft follow a circular path
b) will oppose the tendency of the aircraft to follow a circular path c) will oppose the weight thus re-uiring more total lift in the turn
#. +f$ after a disturbance$ an aeroplane initially returns to its e-uilibrium state a) it has neutral stability
b) it has static stability and may be dynamically stable c) it is neutrally unstable
%. ,tability of an aircraft is
a) the tendency of the aircraft to return to its original trimmed position after ha/ing been displaced b) the ability of the aircraft to rotate ab out an axis
c) the tendency of the aircraft to stall at low airspeeds
'. 0ith reference to altimeters F(E is
a) setting aerodrome atmospheric pressure so that an altimeter reads ;ero on landing and ta"e off b) -uite fine e-uipment
c) the manufacturers registered name
. Jnder the +6AO HFI code there are which three settings a) F(E $ F: $ FE
b) FE( $ F: $ FE c) FE $ F $ FFE
. 0ing loading is
a) 7>O,, 0E+7:* di/ided by 7>O,, 0+7 A>EA b) 0+7 A>EA x 0+7 6:O>4
c) the ultimate tensile strength of the wing
8. *he three axes concerned with stability of an aircraft ha/e
a) normal axis through 6 of 7. ateral axis & wing tip to wing tip. ongitudinal axis & nose to tail but not through 6 of 7
b) longitudinal$ lateral and normal axis all passing through aircraft centre of gra/ity
c) longitudinal axis nose to tail$ lateral axis at furthest span point$ normal axis through centre of pressure
. A barometer indicates a) pressure b) density c) temperature
13. +f an aircraft returns to a position of e-uilibrium it is said to be a) negati/ely stable
b) neutrally stable c) positi/ely stable
Module 8 Exam 22 Aerodynamics
1. *he pendulum effect on a high wing aircraft a) increases lateral stability
b) decreases lateral stability c) has no effect on lateral stability
2. *he amount of water /apour capacity in the air !humidity holding capacity of the air) is a) greater on a colder day$ and lower on a hotter day
b) greater on a hotter day and lower on a colder day c) doesnKt ha/e a significant difference
#. 0eight is e-ual to a) /olume x gra/ity b) mass x acceleration c) mass x gra/ity
%. +nduced drag
a) increases with an increase in speed
b) reduces with an increase in angle of attac" c) increases with increase in aircraft weight
'. Airflow o/er the upper surface of the wing generally a) flows towards the root
b) flows towards the tip
c) flows straight from leading edge to trailing edge
. 0ith an increase in aspect ratio for a gi/en +A,$ induced drag will a) remain constant
b) increase c) reduce
. 0ith increasing altitude the angle at which a wing will stall a) remains the same
b) reduces c) increases
8. +f the density of the air is increased$ the lift will a) increase
b) decrease
c) remain the same
. All the factors that affect the lift produced by an aerofoil are a) angle of attac"$ air density$ /elocity$ wing area b) angle of attac"$ air temperature$ /elocity$ wing area
c) angle of attac"$ /elocity$ wing area$ aerofoil shape$ air density
13. A wing section suitable for high speed would be a) thic" with high camber
b) thin with high camber c) thin with little or no camber
Module 8 Exam 2# Aerodynamics
1. *he induced drag of an aircraft
a) increases with increasing speed b) increases if aspect ratio is increased c) decreases with increasing speed
2. As the speed of an aircraft increases the profile drag a) increases
b) decreases
c) decreases at first then increase
#. *he stagnation point on an aerofoil is the point where a) the suction pressure reaches a maximum
b) the boundary layer changes from laminar to turbulent c) the airflow is brought completely to rest
%. After a disturbance in pitch$ an aircraft continues to oscillate at constant amplitude. +t is a) longitudinally unstable
b) longitudinally neutrally stable c) laterally unstable
'. On an aircraft with an all&mo/ing tailplane nose up pitch is caused by a) increasing tailplane incidence
b) decreasing tailplane incidence c) up mo/ement of the trim tab
. *he stalling of an aerofoil is affected by the a) airspeed
b) angle of attac" c) transition speed
. 0hat gi/es the aircraft directional stability a) @ertical stabiliser
b) :ori;ontal stabiliser c) Ele/ators
8. *he most fuel efficient of the following types of engine is the a) roc"et
b) turbo&=et engine c) turbo&fan engine
. *he -uietest of the following types of engine is the a) roc"et
b) turbo&=et engine c) turbo&fan engine
13. (orward motion of a glider is pro/ided by a) the engine
b) the weight c) the drag
Module 8 Exam 2% Aerodynamics
1. 5rofile drag consists of what drag types a) (orm$ s"in friction and interference b) (orm$ induced and s"in friction c) (orm$ induced and interference
2. An aircraft in straight and le/el flight is sub=ect to a) ;ero load factor
b) a load factor of 1 c) a load factor of 1<2
#. Aspect ratio is gi/en by the formula a) Mean 6hord ,pan b) ,pan2 Area c) ,pan2 Mean 6hord
%. On a high wing aircraft in a turn
a) the up going wing loses lift which has a de&stabili;ing effect b) the down going wing gains lift causing a stabili;ing effect c) the down going wing loses lift causing a de &stabili;ing effect
'. 0hich condition is the actual amount of water /apour in a mixture of air and water a) >elati/e humidity
b) 4ew point
c) Absolute humidity
. An aspect ratio of 8 means
a) the span is 8 times the mean chord b) the mean chord is 8 times the span c) the area is 8 times the span
. +n a turn$ if your centrifugal force is greater than the hori;ontal component of lift a) ou are slipping
b) ou are s"idding
c) ou are in a coordinated turn
8. 0hich will weigh the least
a) 8 parts of dry air and 2 parts of water /apour b) #' parts of dry air and ' parts of water /apour c) '3 parts of dry air and '3 parts of water /apour
. A high aspect ratio wing
a) is stiffer than a low aspect ratio wing
b) has less induced drag than a low aspect ratio wing c) has a higher stall angle than a low aspect ratio wing
13. *he thrust line of an engine may be set slightly to the right on aircraft manufacture to a) counteract the turning tendency due to propeller tor-ue
b) assist in a climbing turn c) pre/ent hori;ontal oscillation
Module 8 Exam 2' Aerodynamics
1. +nduced downwash
a) reduces the effecti/e angle of attac" of the wing b) increases the effecti/e angle of attac" of the wing c) has no effect on the angle of attac" of the wing
2. 4uring a turn$ the stalling angle a) increases
b) decreases
c) remains the same
#. 0hich is the ratio of the water /apour actually present in the atmosphere to the amount that would be present if the air were saturated at the pre/ailing temperature and pressure
a) Absolute humidity b) >elati/e humidity c) 4ew point
%. A straight rectangular wing$ without any twist$ will a) ha/e greater angle of attac" at the tip
b) ha/e the same angle of attac" at all points along the span c) ha/e less angle of attac" at the tip
'. 7i/en 2 wings$ the first with a span of 12m and a chord of 2 m. *he second has a span of m and a chord of 1m. :ow do their Aspect >atios compare
a) *he first is higher b) *he second is higher c) *hey are the same
. *he 6 of 7 mo/es in flight. *he most li"ely cause of this is a) mo/ement of passengers
b) mo/ement of cargo
c) consumption of fuel and oils
. *he speed of sound in the atmosphere
a) /aries according to the fre-uency of the sound b) changes with a change in temperature
c) changes with a change in pressure
8. A straight rectangular wing$ without any twist$ will a) stall first at the tip
b) stall first at the root
c) stall e-ually along the span of the wing
. 0hat is sea le/el pressure a) 131#.2 mb
b) 1312.# mb c) 13#2.2 mb
13. 0hich atmospheric conditions will cause the true landing speed of an aircraft to be the greatest a) ow temperature with low humidity
b) :igh temperature with low humidity c) :igh temperature with high h umidity
Module 8 Exam 2 Aerodynamics
1. +n flight if your aircraft nose gets an upward gust of wind$ what characteristic will ha/e the greatest effect to counteract it
a) :ori;ontal stabiliser and fuselage length b) 0ing ,weep
c) 5osition of the centre of pressure relati/e to the centre of gra/ity
2. 0hen the weight of an aircraft increases$ the minimum drag speed a) decreases
b) increases
c) remains the same
#. 0hich statement concerning heat and<or temperature is true
a) *here is an in/erse relationship between temperature and heat.
b) *emperature is a measure of the "inetic energy of the molecules of any substance c) *emperature is a measure of the potential energy of the molecules of any substance
%. *o correct dutch roll you must damp oscillation aroundD a) *he /ertical axis
b) *he lateral axis c) *he longitudinal axis
'. 0hen an aircraft experiences induced drag
a) air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root b) air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip c) either a) or b) since induced drag does not cause spanwise flow
. 0hat is absolute humidity
a) *he temperature to which humid air must be cooled at constant pressure to become saturated. b) *he actual amount of the water /apour in a mixture of air and water
c) *he ratio of the water /apour actually present in the atmosphere to the amount that would be present if the air were saturated at the pre/ailing temperature and pressure
. +f the load factor on an aircraft is 2$ the stall speed is a) increased
b) decreased c) stays the same
8. An ele/ator trim tab is used to
a) pre/ent the control surface from stalling the airflow b) reduce control column forces on the pilot
c) counteract propeller tor-ue
. On a power cur/e graph the intersection of a/ailable power and re-uired power against speed gi/es the a) most efficient cruise speed
b) minimum drag speed
c) the aircraftKs maximum speed
13. An aeroplane wing is designed to produce lift resulting from relati/ely a) positi/e air pressure below and abo/e the wingKs surface
b) negati/e air pressure below the wingKs surface and positi/e air pressure abo/e the wingKs surface c) positi/e air pressure below the wingKs surface and negati/e air pressure abo/e the wingKs surface
Module 8 Exam 2 Aerodynamics
1. Aspect ratio of a wing is defined as the ratio of the a) wingspan to the wing root
b) s-uare of the chord to the wingspan c) wingspan to the mean chord
2. 0hich of the following is true
a) ift acts at right angles to the wing chord line and weight acts /ertically down b) ift acts at right angles to the relati/e airflow and weight acts /ertically down
c) ift acts at right angles to the relati/e airflow and weight acts at right angles to the aircraft centre line
#. *he temperature to which humid air must be cooled at constant pressure to become saturated is called a) dewpoint
b) absolute humidity c) relati/e humidity
%. *he airflow o/er the upper surface of a cambered wing a) increases in /elocity and pressure
b) increases in /elocity and reduces in pressure c) reduces in /elocity and increases in pressure
'. 0hich type of flap increases the area of the wing a) 5lain (lap
b) (owler (lap c) All flaps
. +f all$ or a significant part of a stall strip is missing on an aeroplane wing$ a li"ely result will be a) increased lift in the area of installation on the opposite wing at high angles of attac" b) asymmetrical aileron control at low angles of attac"
c) asymmetrical aileron control at or near stall angles of attac"
. 0ith increased speed in le/el flight a) induced drag increases b) profile drag increases
c) profile drag remains constant
8. 4eployment of flaps will result in a) a decrease in stall angle b) an increase in stall angle c) a decrease in angle of attac"
. An aeroplane wing is designed to produce lift resulting from relati/ely a) positi/e air pressure below and abo/e the wingKs surface.
b) negati/e air pressure below the wingKs surface and positi/e air pressure abo/e the wingKs surface. c) positi/e air pressure below the wingKs surface and negati/e air pressure abo/e the wingKs surface.
13. *he angle of attac" of an aerofoil section is the angle between the a) chord line and the relati/e airflow
b) underside of the wing surface and the mean airflow c) chord line and the centre line of the fuselage
Module 8 Exam 28 Aerodynamics
1. A swept wing tends to stall first at the a) root
b) tip
c) centre section
2. Greuger (laps are normally fitted to a) the trailing edge of the wings b) the tips of the wings
c) the leading edge of the wings
#. 7i/en an aircraft with positi/e dihedral in a left turn$ what wing will ha/e the bigger angle of attac" a) eft
b) >ight c) either
%. *he trailing /ortex on a pointed wing !taper ratio C 3) is a) at the root
b) at the tip
c) e-ually all along the wing span
'. A high wing aircraft will be more
a) laterally stable than a low wing aircraft b) longitudinally stable than a low wing aircraft c) directionally stable than a low wing aircraft
. A wing with a /ery high aspect ratio !in comparison with a low aspect ratio wing) will ha/e a) increased drag at high angles of attac"
b) a high stall speed
c) poor control -ualities at low airspeeds
. *he lift cur/e for a delta wing is
a) more steep than that of a high aspect ratio wing b) less steep than that of a high aspect ratio wing c) the same as that of a high aspect ratio wing
8. After an aircraft has been disturbed from its straight and le/el flight$ it returns to its original attitude with a small amount of decreasing oscillation. *he aircraft is
a) statically stable but dynamically unstable b) statically unstable but dynamically stable c) statically stable and dynamically stable
. An increase in the speed at which an aerofoil passes through the air increases lift because
a) the increased speed of the airflow creates a greater pressure differential between the upper and lower surfaces.
b) the increased speed of the airflow creates a lesser pressure differential between the upper and lower surfaces.
c) the increased /elocity of the relati/e wind increases the angle of attac"
13. A delta wing has
a) a higher stall angle than a straight wing b) a lower stall angle than a straight wing c) the same stall angle than a straight wing
Module 8 Exam 2 Aerodynamics
1. *he ift<4rag ratio of a wing at the stalling angle is a) of a negati/e /alue
b) low c) high
2. *he airflow o/er the upper surface of a cambered wing a) increases in /elocity and pressure
b) increases in /elocity and reduces in pressure c) reduces in /elocity and increases in pressure
#. *he speed of air o/er a swept wing which contributes to the lift is a) less than the aircraft speed
b) more than the aircraft speed c) the same as the aircraft speed
%. (or a gi/en angle of attac" induced drag is a) greater on a high aspect ratio wing b) greater towards the wing root c) greater on a low aspect ratio wing
'. +n straight and le/el flight$ the angle of attac" of a swept wing is a) the same as the aircraft angle to the hori;ontal
b) more than the aircraft angle to the hori;ontal c) less than the aircraft angle to the hori;ontal
. +nduced drag
a) is ne/er e-ual to the profile drag
b) is e-ual to the profile drag at the stalling speed c) is e-ual to the profile drag a t @md
. A delta wing aircraft flying at the same speed !subsonic) and angle of attac" as a swept wing aircraft of similar wing area will produce
a) the same lift b) more lift c) less lift
8. *he stagnation point is
a) static pressure plus dynamic pressure b) static pressure minus dynamic pressure c) dynamic pressure only
. On a swept wing aircraft$ due to the ad/erse pressure gradient$ the boundary layer on the upper surface of the wing tends to flow
a) directly from leading edge to trailing edge b) towards the tip
c) towards the root
13. 0ith increased speed in le/el flight a) induced drag increases b) profile drag increases
Module 8 Exam #3 Aerodynamics
1. +f a swept wing stalls at the tips first$ the aircraft will a) pitch nose up
b) pitch nose down c) roll
2. *he thic"ness<chord ratio of the wing is also "nown as a) aspect ratio
b) mean chord ratio c) fineness ratio
#. (lexure of a rearward swept wing will
a) increase the lift and hence increase the flexure b) decrease the lift and hence decrease the flexure c) increase the lift and hence decrease the flexure
%. A :igh Aspect >atio wing is a wing with a) long span$ long chord
b) long span$ short chord c) short span$ long chord
'. ,tall commencing at the root is preferred because a) the ailerons become ineffecti/e
b) it pro/ides the pilot with a warning of complete loss of lift c) it will cause the aircraft to pitch nose up
. An aircraft flying in Hground effectI will produce
a) more lift than a similar aircraft outside of ground effect b) less lift than a similar aircraft outside of ground effect c) the same lift as a similar aircraft outside of ground effect
. +f the angle of attac" of a wing is increased in flight$ the a) 6 of 5 will mo/e forward
b) 6 of 7 will mo/e aft c) 6 of 5 will mo/e aft
8. *he >ams :orn @ortex on a forward swept wing will be a) the same as a rearward swept wing
b) more than a rearward swept wing c) less than a rearward swept wing
. 0hen maintaining le/el flight an increase in speed will a) cause the 6 of 5 to mo/e aft
b) cause the 6 of 5 to mo/e forward
c) ha/e no affect on the position of the 6 of 5
13. (or a cambered wing section the ;ero lift angle of attac" will be a) ;ero
b) % degrees c) negati/e
Module 8 Exam #1 Aerodynamics
1. 4ensity changes with altitude at a rate a) of 2"g<m# per 1333ft
b) which changes with altitude c) which is constant until 11"m
2. Airflow at subsonic speed is ta"en to be a) compressible
b) incompressible
c) either a or b depending on altitude
#. ?ernoulliKs e-uation shows that
a) at constant /elocity the "inetic energy of the air changes with a change of height b) with a change in speed at constant height both "inetic and potential energies change c) with a change in /elocity at constant height the static pressure will change
%. +f fluid flow through a /enturi is said to be incompressible$ the speed of the flow increases at the throat to a) maintain a constant /olume flow rate
b) allow for a reduction in static pressure c) allow for an increase in static pressure
'. *o produce lift$ an aerofoil must be a) asymmetrical
b) symmetrical
c) either a or b abo/e
. ift is dependent on
a) the area of the wing$ the density of the fluid medium$ and the s-uare of the /elocity b) the net area of the wing $the density of the fluid medium and the /elocity
c) the frontal area of the wing$ the density of the fluid medium and the /elocity
. *he maximum lift<drag ratio of a wing occurs
a) at the angle of attac" where the wing de/elops its maximum lift b) during ta"e off
c) at an angle below which the wing de/elops max lift
8. A wing de/elops 13$333 of lift at 133"nots. Assuming the wing remains at the same angle of attac" and remains at the same altitude$ how much lift will it de/elop at #33"nots
a) 33$333 b) 3$333 c) #3$333
. *he angle of attac" is
a) related to angle of incidence b) always "ept below 1' degrees c) not related to the angle of incidence
13. *he difference between the mean camber line and the chord line of an aerofoil is a) one is always straight and the other may be straight
b) neither are straight c) they both may be cur/ed
Module 8 Exam #2 Aerodynamics
1. +f the 6 of 7 is calculated after loading as within limits for ta"e off a) no further calculation is re-uired
b) a further calculation is re-uired prior to landing to al low for fuel and oil consumption c) a further calculation is re-uired prior to landing to allow for flap deployment
2. A stalled aerofoil has a lift<drag ratio
a) more than the lift<drag ratio prior to s tall b) ;ero
c) less than the lift<drag ratio prior to stall
#. At low forward speed
a) increased downwash reduces tailplane effecti/eness b) increased downwash increases tailplane effecti/eness c) excessi/e rudder mo/ement may cause fin to stall
%. :elicopter rotor blades create lift by
a) creating low pressure abo/e the blades b) pushing the air down
c) wor"ing li"e a screw
'. On some modern aircraft a stall warning will automatically a) increase thrust
b) extend outboard slats
c) cause a pitch nose down mo/ement
. Abo/e '$833 ft temperature
a) remains constant up to 11'$333ft b) decreases by 1.8o6 up to 11'333ft c) increases by 3.#3#o6 up to 11'333ft
. At sea le/el$ +,A atmospheric pressure is a) 1%. 5,+
b) 1%. Gpa c) 13 ?ar
8. *he spanwise component of the airflow is a) greater at higher speeds
b) less at higher speeds c) unaffected by speed
. A wing fence
a) increases lateral control b) acts as a lift dumping de/ice
c) reduces spanwise flow on a swept wing thus reducing induced drag
13. *he highest lift<drag ratio is greatest at a) low altitudes
b) the point =ust before the stalling angle c) the optimum angle of attac"
Module 8 Exam ## Aerodynamics
1. 0ith all conditions remaining the same$ if the aircraft speed is hal/ed$ by what factor is the lift reduced a) :alf
b) ?y a factor of % c) >emains the same
2. *he boundary layer o/er an aerofoil is
a) a layer of air close to the aerofoil that is stationary
b) a layer of air close to the aerofoil which is mo/ing at a /elocity less than free stream air
c) a layer of turbulent air close to the aerofoil which is mo/ing at a /elocity less than free stream air
#. On a swept wing aircraft$ the fineness ratio of an aerofoil is a) highest at the root
b) highest at the tip
c) e-ual throughout the span
%. +A, for a stall will
a) increase with altitude b) decrease with altitude
c) roughly remain the same for all altitude
'. +f the radius of a turn is reduced the load factor will a) increase
b) decrease
c) remain the same
. ,treamlining will reduce a) form drag
b) induced drag c) s"in friction drag
. +f an aircraft has a gross weight of #333 "g and is then sub=ected to a total weight of 333 "g the load factor will be
a) 27 b) #7 c) 7
8. A constant rate of climb is determined by a) weight
b) wind speed
c) excess engine power
. +ce formed on the leading edge will cause the aircraft to a) stall at the same stall speed and AoA
b) stall at a lower speed c) stall at a higher speed
13. 0ith an aircraft in ban"$ the upper wing produces more drag. *o compensate a) the rudder is operated
b) when ban" angle is achie/ed then the ailerons are operated in the opposite direction to cause the opposite effect
Module 8 Exam #% Aerodynamics
1. +f both wings lose lift the aircraft a) pitches nose up
b) pitches nose down
c) glides on a hori;ontal plane
2. Jnder what conditions will an aircraft create best lift a) 6old dry day at 233 ft
b) :ot damp day at 1233 ft c) 6old wet day at 1233 ft
#. +f there is an increase of density$ what effect would there be in aerodynamic dampening a) one
b) 4ecreased c) +ncreased
%. As Mach number increases$ what is the effect on boundary layer a) ?ecomes more turbulent
b) ?ecomes less turbulent c) 4ecreases in thic"ness
'. 0hen a slat is retracted it mo/es
a) towards the upper leading edge of the wing b) towards the lower leading edge of the wing
c) towards the center of the leading edge of the wing
. +n a turn the up&going wing causes a
a) de&stabilising effect due to increased AoA b) de&stabilising effect due to decreased AoA c) stabilising effect due to decreased AoA
. *he stagnation point consists of
a) dynamic and static air pressure b) static air pressure
c) dynamic air pressure
8. 4uring a glide the following forces act on an aircraft a) lift$ weight$ thrust
b) lift$ drag$ weight c) lift and weight only
. awing is a rotation around
a) the normal axis obtained by the ele/ator b) the lateral axis obtained by the rudder c) the normal axis obtained by the rudder
13. +f an aileron is mo/ed downward
a) the stalling angle of that wing is increased b) the stalling angle of that wing is decreased
