[App Bug Report] Figure missing #247
Description
Description
The figure is missing
Data
href : https://www.chair-flight.com/modules/atpl/tests/YDJMsHra/study
test-current-question: &a1
questionId: dFYWD92j
templateId: QCVDAMOF
seed: jy7FoqFp
type: multiple-choice
question: |-
Refer to figure.
The high lift device shown in the figure 2 is a:
annexes: []
correctOptionId: OYOKOB8XH
options:
- id: OUKJPU67O
text: slotted flap.
why: ""
- id: O4DIZOISB
text: Krueger flap.
why: ""
- id: OYOKOB8XH
text: slat.
why: ""
- id: OXDZ2O0PS
text: Fowler flap.
why: ""
explanation: ""
test:
id: YDJMsHra
questionBank: atpl
title: 081 study
status: started
mode: study
currentQuestionIndex: 9
timeSpentInMs: 225993
durationInMs: 2400000
questions:
- questionId: MW5JTYj4
templateId: QCTBA5LPR
seed: jGhV9pUK
type: multiple-choice
question: The Lift Coefficient versus Angle Of Attack curve of a symmetrical
aerofoil section intersects the horizontal axis of the graph...
annexes: []
correctOptionId: OYN0X7PUC
options:
- id: OULUZ3IPP
text: to the left of the origin.
why: ""
- id: OTBBUUHXD
text: at no point.
why: ""
- id: OPMN6WNDI
text: to the right of the origin.
why: ""
- id: OYN0X7PUC
text: at the origin.
why: ""
explanation: ""
selectedOptionId: OYN0X7PUC
- questionId: 15AWRLiD
templateId: QUNWMLDB
seed: EJcgj3zn
type: multiple-choice
question: >-
Which of these statements about the strength of wing tip vortices are
correct or incorrect?
1) Assuming no flow separation, the strength of wing tip vortices
increases as the angle of attack decreases.
2) The strength of wing tip vortices increases as the aspect ratio
decreases.
annexes: []
correctOptionId: pfdASAvE
options:
- id: cHAwN1Dj
text: One is correct, two is correct
why: ""
- id: ypGli4sn
text: One is correct, two is incorrect
why: ""
- id: pfdASAvE
text: One is incorrect, two is correct
why: ""
- id: NJitxPM3
text: One is incorrect, two is incorrect
why: ""
explanation: ""
selectedOptionId: pfdASAvE
- questionId: xORzsKVz
templateId: QYMTA66GP
seed: XqcwPVMt
type: multiple-choice
question: Why is there a limit on the full rudder deflection as airspeed (IAS)
increases on transport aeroplanes?
annexes: []
correctOptionId: OPTDIV2FR
options:
- id: OPTDIV2FR
text: Because full rudder deflection could create an excessive load on the
structure.
why: ""
- id: ONZPYNEDZ
text: Full rudder deflection is not to be limited on transport aeroplanes as
airspeed increases.
why: ""
- id: OBHTNKHQT
text: To reduce the risk of entering a spiral divergence in cruise.
why: ""
- id: OE39RLMNG
text: To reduce the directional stability at high airspeed.
why: ""
explanation: ""
selectedOptionId: OPTDIV2FR
- questionId: RZt2T5k2
templateId: QIBARSUP
seed: fMGiJSTL
type: multiple-choice
question: "The (subsonic) static pressure:"
annexes: []
correctOptionId: OFKXQGCFZ
options:
- id: OP2FXEBZ4
text: is the total pressure plus the dynamic pressure.
why: ""
- id: OHGTMLBXX
text: is the pressure in a point at which the velocity has become zero.
why: ""
- id: OFKXQGCFZ
text: decreases in a flow in a tube when the diameter decreases.
why: ""
- id: O66AABQ6T
text: increases in a flow in a tube when the diameter decreases.
why: ""
explanation: ""
selectedOptionId: OFKXQGCFZ
- questionId: 8RFE3uT4
templateId: QCYMWTXP
seed: zcsO0MYK
type: multiple-choice
question: Where is the Centre of Pressure (CP) in relation to the Aerodynamic
Centre (AC) on a positively cambered aerofoil?
annexes: []
correctOptionId: OMPLSHVHU
options:
- id: OMPLSHVHU
text: The CP is behind the AC.
why: ""
- id: OKFUVXORC
text: The position of the AC is independent of the position of the CP.
why: ""
- id: OCF5DEIGK
text: The CP is above the AC.
why: ""
- id: ORJV4OCCN
text: The CP is ahead of the AC.
why: ""
explanation: ""
selectedOptionId: OMPLSHVHU
- questionId: cIXj78qu
templateId: QRHFBDPL
seed: ddcXinjV
type: multiple-choice
question: Which of the following are most effective at reducing induced drag?
annexes: []
correctOptionId: OELU8AAZA
options:
- id: OELU8AAZA
text: Higher Aspect Ratio and winglets.
why: ""
- id: OEU82NG6P
text: Lower Aspect Ratio and wing fences.
why: ""
- id: O25FHSD2R
text: Higher Aspect Ratio and removal of winglets.
why: ""
- id: OJKWQGG4V
text: Lower Aspect Ratio and flaps.
why: ""
explanation: ""
selectedOptionId: OELU8AAZA
- questionId: LzUzWT87
templateId: QYXQONLL
seed: pbCQ85Wd
type: multiple-choice
question: An aeroplane is established on final approach descending through 1000
ft when the pilot realizes that the aeroplane is about to enter an area
of heavy tropical rain. The pilot must consider that the stalling…
annexes: []
correctOptionId: OQJBK0F96
options:
- id: OQJBK0F96
text: speed increase due to the CLMAX reduction because of water distorting the
shape of the airfoil and the airflow pattern.
why: ""
- id: ONDTK3Y45
text: angle of attack decreases due to the associated gusts from the heavy
downpour of rain.
why: ""
- id: OTA6DFJG5
text: angle of attack decrease due to the apparent decrease of the load factor
from the heavy downpour of rain.
why: ""
- id: OY9UUWJ2E
text: speed increase due to compressibility effects appearing earlier than
normal because of the concentration of water on the wings.
why: ""
explanation: ""
selectedOptionId: OQJBK0F96
- questionId: mrVVXMf9
templateId: QDEH1U43J
seed: ysTcIuHw
type: multiple-choice
question: >-
Consider a jet transport aircraft flying in icing conditions, which two
statements below are correct with regards to unexpected stalls?
1\. The pitot and static ports can become frozen over causing a lack of
information to the ADC and subsequently a lack of warning to the pilots
when the critical AoA is reached.
2\. The large amount of ice forming on the tail plane causes an increase in mass and thus an uncontrollable pitch up.
3\. The flow-back ice forming on the wings will decrease the critical AoA leading to an unexpected stall.
4\. Ice formation on the main fuselage body will be more critical in causing a stall vs ice formation on the wings.
annexes: []
correctOptionId: O2XGCGWVV
options:
- id: OEGVAUZ4L
text: 2 and 3
why: ""
- id: O2NT8H1NB
text: 2 and 4
why: ""
- id: OAR4YZP3Z
text: 1 and 4
why: ""
- id: O2XGCGWVV
text: 1 and 3
why: ""
explanation: ""
selectedOptionId: O2XGCGWVV
- questionId: QO5PDgrR
templateId: QXDTGCX4G
seed: xjcPLvBH
type: multiple-choice
question: >-
Which of these statements about the effect of wing sweep on centre of
pressure location are correct or incorrect?
1) The centre of pressure on an unswept wing moves aft as the angle of
attack approaches and exceeds the critical angle of attack.
2) When sweep back increases, the centre of pressure has an increased
tendency to move forward as the angle of attack approaches and exceeds
the critical angle of attack.
annexes: []
correctOptionId: TPGVRNOD
options:
- id: TPGVRNOD
text: One is correct, two is correct
why: ""
- id: DiZhF5WF
text: One is correct, two is incorrect
why: ""
- id: 1UF8TALX
text: One is incorrect, two is correct
why: ""
- id: wtYnU69N
text: One is incorrect, two is incorrect
why: ""
explanation: ""
selectedOptionId: DiZhF5WF
- *a1
- questionId: YzcorB9b
templateId: QDNEXIXX
seed: YiuMBPbv
type: multiple-choice
question: 'On a wing fitted with a "Fowler" type trailing edge flap, the "Full
extended" position will produce:'
annexes: []
correctOptionId: OZPZS5VCI
options:
- id: OZPZS5VCI
text: an increase in wing area and camber.
why: ""
- id: OL1DPOR9Z
text: an unaffected wing area and increase in camber.
why: ""
- id: ORFKM8NSF
text: an unaffected CD, at a given angle of attack.
why: ""
- id: OQXXJNXBQ
text: an increase in wing area only.
why: ""
explanation: ""
- questionId: jdVJlKaT
templateId: QTXCBXQC
seed: fk5Zh243
type: multiple-choice
question: An aircraft with dirt on the airframe is subject to what type of drag?
annexes: []
correctOptionId: OJNTEHQSZ
options:
- id: O9URC0XNX
text: Form Drag
why: ""
- id: OU4KX6TH0
text: Decrease Parasite Drag
why: ""
- id: OJNTEHQSZ
text: Friction Drag
why: ""
- id: O28UKC1MH
text: Less Induced Drag
why: ""
explanation: ""
- questionId: YJmD3lS6
templateId: QBKHK1PWD
seed: P1833Dku
type: multiple-choice
question: Why are Vortex generators mounted on the upper wing surface?
annexes: []
correctOptionId: OPVOPJFLC
options:
- id: ORNOCBVEH
text: To decrease the stall speed by increasing spanwise flow over the wing
why: ""
- id: OZDHPWJBJ
text: To combat the interference drag of the trailing edge flaps
why: ""
- id: OPVOPJFLC
text: To energise the boundary layer
why: ""
- id: O5TD8XMFB
text: To increase the effectiveness of the spoiler due to increase in parasite
drag
why: ""
explanation: ""
- questionId: aCquOkDA
templateId: QFEPCRMDY
seed: yzvMLF2v
type: multiple-choice
question: Which type of flap is shown in the picture 4?
annexes:
- /content/atpl/media/ABFVDW7.jpg
correctOptionId: OKHLE4J95
options:
- id: O9DGNVHLO
text: Slotted flap
why: Correct definition for "2".
- id: OCWPCSGEE
text: Plain flap
why: Correct definition for "1".
- id: OQ5O0HUAP
text: Fowler flap
why: Correct definition for "3".
- id: OKHLE4J95
text: Split flap
why: ""
explanation: ""
- questionId: pfcSD4nG
templateId: QGDKPRAE
seed: UcojIB7S
type: multiple-choice
question: "The subsonic speed range:"
annexes: []
correctOptionId: O8IEEUQ34
options:
- id: O4GBNWZ4W
text: ends at M = 1.
why: ""
- id: O79BAGJHS
text: implies both subsonic and supersonic speeds exist in the flow around the
aeroplane.
why: ""
- id: OTUVN2TAP
text: ends at a Mach number just above M = 1.
why: ""
- id: O8IEEUQ34
text: ends at MCRIT.
why: ""
explanation: ""
- questionId: gp3eme6S
templateId: QHXGCXYW
seed: 70WYobMd
type: multiple-choice
question: >-
Refer to figure.
What is the correct combination of letters identifying the airfoils with
the corresponding numbers from the CD graphic?
annexes:
- /content/atpl/media/AV67ZFMKO.jpg
correctOptionId: O8GGEZICM
options:
- id: O8GGEZICM
text: 1 – d, 2 – a, 3 – c, 4 – b
why: ""
- id: OKQY6ASHO
text: 1 – a, 2 – b, 3 – c, 4 – d
why: ""
- id: OV75FRETK
text: 1 – d, 2 – a, 3 – b, 4 – c
why: ""
- id: OPWCBI0PS
text: 1 – a, 2 – d, 3 – c, 4 – b
why: ""
explanation: ""
- questionId: IoC7XWuf
templateId: QEDL6JADI
seed: OVe158UK
type: multiple-choice
question: >-
Refer to figure.
The trailing edge flaps are stuck in the position shown in the picture.
Which high-lift device is causing the asymmetry, and what could be a
possible consequence of this?
annexes:
- /content/atpl/media/ALUAX2WZT.jpg
correctOptionId: OWRCG6ZAC
options:
- id: OVNGKZFGP
text: Slat asymmetry and right-wing stalls
why: ""
- id: OBACXDRI3
text: Slat asymmetry and left-wing stalls
why: ""
- id: OPVDSD8YB
text: Flap asymmetry and right-wing stalls
why: ""
- id: OWRCG6ZAC
text: Flap asymmetry and left-wing stalls
why: ""
explanation: ""
- questionId: n6XzmcZo
templateId: QFOGFEUK
seed: lL8oYqnd
type: multiple-choice
question: When flying with a 1.3 g buffet onset, at what bank angle will buffet
be encountered in a level turn?
annexes: []
correctOptionId: OHCF9ML5M
options:
- id: OUZSJHA0E
text: 28º
why: ""
- id: OOQLHUTMR
text: 37.5º
why: ""
- id: OZZAG69QV
text: 59º
why: ""
- id: OHCF9ML5M
text: 39.72º
why: ""
explanation: ""
- questionId: HpIh2J8n
templateId: QEKBPQLK
seed: slReHUAZ
type: multiple-choice
question: Which of these variables are required to calculate drag from the drag
formula?
annexes: []
correctOptionId: OT17XNAMU
options:
- id: OT17XNAMU
text: Dynamic pressure, drag coefficient and wing area.
why: ""
- id: OS59MBGX8
text: Total pressure and wing area only.
why: ""
- id: ONT9TRSQD
text: Frontal wing area, density and wing loading.
why: ""
- id: O72LYTM2C
text: Angle of attack, aspect ratio and dynamic pressure.
why: ""
explanation: ""
- questionId: 5JvoO8nI
templateId: QBEVAA3RZ
seed: NRk7xebS
type: multiple-choice
question: The boundary layer will separate from the aerofoil immediately...
annexes: []
correctOptionId: OHNDVH74Q
options:
- id: OSL8I3ASR
text: in front of the shock wave on the lower wing surface.
why: ""
- id: OH0473LSM
text: behind the shock wave on the lower wing surface.
why: ""
- id: OHNDVH74Q
text: behind the shock wave on the upper wing surface.
why: ""
- id: OGPD647V8
text: in front of the shock wave on the upper wing surface.
why: ""
explanation: ""
- questionId: PIiM36fG
templateId: QLKIQNW3G
seed: 1G5Ry8yp
type: multiple-choice
question: What happens to the flow velocity over the wing when angle of attack
decreases?
annexes: []
correctOptionId: OXFXEH688
options:
- id: OC2C5FKDU
text: It decreases, and lift capability increases.
why: ""
- id: OXFXEH688
text: It decreases, and lift capability decreases.
why: ""
- id: OIAWC1QGV
text: It increases, and lift capability decreases.
why: ""
- id: OCXQR9RBW
text: It increases, and lift capability increases.
why: ""
explanation: ""
- questionId: eJ68ndSu
templateId: QHMXGLEX
seed: KqMILzUD
type: multiple-choice
question: "During an normal spin recovery:"
annexes: []
correctOptionId: OVMWJXSUL
options:
- id: OZGEOIIMX
text: the control stick is pulled to the most aft position.
why: ""
- id: O9GRZHKB5
text: the control stick is moved side ways, against the angle of bank.
why: ""
- id: OTL0OIWUE
text: the control stick is moved side ways, in the direction of the angle of
bank.
why: ""
- id: OVMWJXSUL
text: the ailerons are held in the neutral position.
why: ""
explanation: ""
- questionId: oaNNTTvc
templateId: QXOCNOUX
seed: kMX1VifA
type: multiple-choice
question: Which of the following creates induced drag on a wing?
annexes: []
correctOptionId: OTAD2HYIT
options:
- id: OTAD2HYIT
text: Angle of attack.
why: ""
- id: ORJ2ZOUN9
text: Ground effect.
why: ""
- id: O7BPC7MJT
text: Turbulence.
why: ""
- id: OQRGQLQVU
text: Airflow around the fuselage and wing root meeting.
why: ""
explanation: ""
- questionId: fnnd5snm
templateId: Q4BNXWR1I
seed: LSqRDnfX
type: multiple-choice
question: Induced drag will decrease if ahead of the wing the upwash...
annexes: []
correctOptionId: OJD35XQZ0
options:
- id: OKIBVP7UG
text: increases because induced angle of attack increases
why: ""
- id: O97SFHABW
text: increases because effective angle of attack increases
why: ""
- id: ODAOVUQ49
text: decreases because effective angle of attack decreases
why: ""
- id: OJD35XQZ0
text: decreases because induced angle of attack decreases
why: ""
explanation: ""
- questionId: MCueqXqc
templateId: QVOTHG4VK
seed: qXQMWQHG
type: multiple-choice
question: In order to keep straight and level, if the airspeed increases, the
EAF is (1) \_\_\_\_\_, the effective AoA is (2) \_\_\_\_\_\_ and the
induced drag is (3) \_\_\_\_\_\_.
annexes: []
correctOptionId: OVYBB5ZXU
options:
- id: OUTTCSHKY
text: (1) shallower, (2) smaller, (3) smaller
why: ""
- id: OBZ86KMU1
text: (1) shallower, (2) greater, (3) greater
why: ""
- id: OVYBB5ZXU
text: (1) shallower, (2) greater, (3) smaller
why: ""
- id: O0NNI6DR8
text: (1) steeper, (2) greater, (3) greater
why: ""
explanation: ""
- questionId: KXj5KmaN
templateId: QVXETIBJ
seed: ery0I7rb
type: multiple-choice
question: "Compared with the clean configuration, the angle of attack at CLMAX
with trailing edge flaps extended is:"
annexes: []
correctOptionId: OJNSZGY4C
options:
- id: OJNSZGY4C
text: smaller.
why: ""
- id: OR2XNTNDP
text: smaller or larger depending on the degree of flap extension.
why: ""
- id: OLNARZGBW
text: larger.
why: ""
- id: OUWT4FT3L
text: unchanged.
why: ""
explanation: ""
- questionId: R71yGDzw
templateId: QJMGAOYY
seed: 2qVJJuum
type: multiple-choice
question: What is the SI unit of measurement for pressure?
annexes: []
correctOptionId: OAHI4AV2H
options:
- id: OPPE3LZ4E
text: kg/m3
why: ""
- id: OQK6HGMQ0
text: lb/gal
why: ""
- id: OAHI4AV2H
text: N/m2
why: ""
- id: O2DQZ1GFE
text: bar/dm2
why: ""
explanation: ""
- questionId: Q39fJgLX
templateId: QZO0WMLLV
seed: rHlMbZCi
type: multiple-choice
question: A pilot is flying an aeroplane manually, in a turn, but forgets to add
thrust and enters a stall. As a first action in order to initiate stall
recovery, the pilot should...
annexes: []
correctOptionId: OLEUXQJOG
options:
- id: OLEUXQJOG
text: Apply nose-down pitch to reduce the angle of attack.
why: ""
- id: O9ZCHONTR
text: Bring the wings level to direct the lift upwards.
why: ""
- id: OLKBU544U
text: Add thrust to increase speed past the stalling speed.
why: ""
- id: O78PTC3SD
text: Apply rudder to raise that dropped wing.
why: ""
explanation: ""
- questionId: GJjpL7F7
templateId: QOEQERPT
seed: nr7y7igK
type: multiple-choice
question: You are planning to take off on runway XX. Field elevation is 52 ft.
Wing span 20 m. At what height is the downwash least?
annexes: []
correctOptionId: OVR15AGA5
options:
- id: OIYBV1JEX
text: 80 ft
why: ""
- id: OVOOWL185
text: 120 ft
why: ""
- id: OSWXRMYV2
text: 60 ft
why: ""
- id: OVR15AGA5
text: 30 ft
why: ""
explanation: ""
- questionId: r6kjfdLP
templateId: QEKJPZAR
seed: ZDEr7bCx
type: multiple-choice
question: |-
Refer to figure.
Arrange the flaps in order of increasing L/D ratio:
annexes:
- /content/atpl/media/AMRLPNSZS.jpg
correctOptionId: OQDCA9CMH
options:
- id: OK9MSGFOB
text: 3, 1, 4, 2
why: ""
- id: OQDCA9CMH
text: 1, 4, 2, 3
why: ""
- id: OSPBYTZNK
text: 2, 4, 1, 3
why: ""
- id: OX6YGZVXC
text: 4, 3, 2, 1
why: ""
explanation: ""
- questionId: GWvLAyoz
templateId: QUGGOTCZL
seed: TKfZwj5R
type: multiple-choice
question: >-
Refer to figure.
Which of the following graphs illustrate the movement of the total drag
curve when the undercarriage is extended?
annexes:
- /content/atpl/media/ALWCIOSRQ.jpg
correctOptionId: OYGTARJ2P
options:
- id: OYLHD5EMG
text: Figure 2
why: ""
- id: OMVU82RQS
text: Figure 1
why: ""
- id: OIJJ7VTMN
text: Figure 3
why: ""
- id: OYGTARJ2P
text: Figure 4
why: ""
explanation: ""
- questionId: b9fcAYt9
templateId: QGJLBMFE
seed: p1LAdwDu
type: multiple-choice
question: Which statement about negative tail stall is correct?
annexes: []
correctOptionId: O5OBRQ28Z
options:
- id: O55RFVPXV
text: Negative tail stall is a stall of the tailplane when the aerodynamic force
is in upward direction.
why: ""
- id: OKXITKJW2
text: Negative tail stall is a stall of the fin with a negative sideslip angle
(nose pointing to the right of the relative airflow).
why: ""
- id: OLMFQ6LXD
text: When negative tail stall occurs, the aeroplane will show an uncontrollable
pitch-up moment.
why: ""
- id: O5OBRQ28Z
text: When negative tail stall occurs, the aeroplane will show an uncontrollable
pitch-down moment.
why: ""
explanation: ""
- questionId: 3KMRGlrt
templateId: QADJ938YV
seed: f6LrVyPu
type: multiple-choice
question: "Assuming no flow separation and no compressibility effects the
location of the centre of pressure of a symmetrical aerofoil section:"
annexes: []
correctOptionId: OK4E1QKBB
options:
- id: OWY7RFY0Q
text: moves backward when the angle of attack decreases.
why: ""
- id: OK4E1QKBB
text: is independent of angle of attack.
why: ""
- id: OIXM4CMWQ
text: moves forward when the angle of attack decreases.
why: ""
- id: OORASJMQ0
text: is at approximately 50% of the chord irrespective of angle of attack.
why: ""
explanation: ""
- questionId: AwnGv4ln
templateId: QERDJQ5RK
seed: hiymtVIH
type: multiple-choice
question: "As angle of attack is increased on a conventional low speed aerofoil
at low subsonic speeds, flow separation normally starts on the:"
annexes: []
correctOptionId: O7EMQWHBB
options:
- id: OCUQ0CKMA
text: lower surface near the trailing edge.
why: ""
- id: OY0JIDTTU
text: upper surface near the leading edge.
why: ""
- id: OAUJ7GRB6
text: lower surface near the leading edge.
why: ""
- id: O7EMQWHBB
text: upper surface near the trailing edge.
why: ""
explanation: ""
- questionId: KsJ1MrVq
templateId: QA40AMHYZ
seed: lzg0XGPP
type: multiple-choice
question: "470 ft/min corresponds to \\_\\_\\_\\_\\_ m/s:"
annexes: []
correctOptionId: O30ZORQFK
options:
- id: O30ZORQFK
text: "2.4"
why: ""
- id: O1ZPZQYEK
text: "8.83"
why: ""
- id: OM2IKOPEH
text: "1.8"
why: ""
- id: OD1LZDEVS
text: "235"
why: ""
explanation: ""
- questionId: hQMdJLMg
templateId: QCGE0X8AH
seed: RU0YI16H
type: multiple-choice
question: What happens to the lift to drag ratio in the transonic regime?
annexes: []
correctOptionId: O93R2JBRM
options:
- id: OJFWNLMAY
text: Increases
why: ""
- id: OOPUS12ZB
text: Stays the same
why: ""
- id: O93UPNIXP
text: Decreases slowly then increases
why: ""
- id: O93R2JBRM
text: Decreases
why: ""
explanation: ""
- questionId: bOceNXK2
templateId: QFPTWEBF
seed: LgtrLpv5
type: multiple-choice
question: "Coefficient of lift is:"
annexes: []
correctOptionId: OMZR5AGCG
options:
- id: OG5KL0GVL
text: A variable depending on thrust and empange
why: ""
- id: OUYF5GJE6
text: A variable depending on wing camber and static pressure
why: ""
- id: OMZR5AGCG
text: A variable depending on dynamic pressure and the wing area
why: ""
- id: OYCN8YIHN
text: A variable depending on static pressure and the wing area
why: ""
explanation: ""
- questionId: 9C4K5SSs
templateId: QWNFVNEAN
seed: MjPxeu6r
type: multiple-choice
question: At speeds above the critical Mach number, vortex generators fitted to
a wing’s upper surface will...
annexes: []
correctOptionId: OZMGPCYZC
options:
- id: OT2CUW0GU
text: reduce the kinetic energy within the boundary layer.
why: ""
- id: OZMGPCYZC
text: retard shock-induced separation.
why: ""
- id: OX0CWNL11
text: increase the stall speed.
why: ""
- id: OQA05A8L2
text: promote shockinduced separation.
why: ""
explanation: ""
- questionId: A8y3K79W
templateId: QLJTBJXT
seed: WD8ePGM1
type: multiple-choice
question: "An aeroplane is executing a missed approach after entering a
microburst on the approach. The aeroplane may be very close to the stall
due to the:"
annexes: []
correctOptionId: OLA5IRIQ9
options:
- id: OLA5IRIQ9
text: Increasing tailwind.
why: ""
- id: OMZMHFS7A
text: Initial reduction in the rate of descent.
why: ""
- id: OBYN7IIPW
text: Energy gain.
why: ""
- id: OGC6BGRQP
text: Increasing airspeed.
why: ""
explanation: ""
- questionId: LxL1kTaL
templateId: QUXWNWGXS
seed: K6DYP38s
type: multiple-choice
question: |-
Refer to figure.
Choose the correct statement:
annexes:
- /content/atpl/media/A0XA6YE0Z.jpg
correctOptionId: ORM0CBZUG
options:
- id: O20ICIFE2
text: Aerofoil 4 corresponds to line 3.
why: ""
- id: ORM0CBZUG
text: Aerofoil 3 corresponds to line 1.
why: ""
- id: ONVUT4SXZ
text: Aerofoil 3 corresponds to line 2.
why: ""
- id: O5VPSYWPU
text: Aerofoil 1 corresponds to line 4.
why: ""
explanation: ""
- questionId: WYp5tHDl
templateId: QQKQVRHJ
seed: 18zrsd5n
type: multiple-choice
question: What is the effect on landing speed when a trimmable horizontal
stabiliser jams at high IAS?
annexes: []
correctOptionId: O43BMIOWR
options:
- id: O43BMIOWR
text: In most cases, a higher than normal landing speed is required.
why: ""
- id: OBYUYMHRN
text: No effect when landing on a high elevation runway.
why: ""
- id: O99ZJY9TY
text: No effect with a forward CG.
why: ""
- id: OTF6KIMSV
text: In most cases, no effect.
why: ""
explanation: ""
- questionId: 94pKeCjs
templateId: QIAXWZUP
seed: sEgYQdCe
type: multiple-choice
question: "An aeroplane performs a steady horizontal, co-ordinated turn with 45
degrees of bank at 230 kt TAS. The same aeroplane with the same bank
angle and speed, but at a lower mass will turn with:"
annexes: []
correctOptionId: O0LRXKGQF
options:
- id: O0LRXKGQF
text: the same turn radius.
why: ""
- id: OMCHTAMP9
text: a higher rate of turn.
why: ""
- id: OH9YDX0XQ
text: a larger turn radius.
why: ""
- id: OXRWCTDK7
text: a smaller turn radius.
why: ""
explanation: ""
- questionId: xtj4ZDFC
templateId: QHER4MIFG
seed: sLimHpQX
type: multiple-choice
question: "The speeds VNE and VMO refer to, respectively:"
annexes: []
correctOptionId: O3HU3CGYK
options:
- id: O3HU3CGYK
text: VNE refers to pistons and VMO refers to jets.
why: ""
- id: OK7MV8PBH
text: They can both refer to piston and jet aircraft.
why: ""
- id: OKYTRZZXD
text: VNE refers to jets and VMO refers to pistons.
why: ""
- id: OHXNOZ0XI
text: They both apply to piston jet aircraft only.
why: ""
explanation: ""
- questionId: xMK2XUHz
templateId: QGGBIADH
seed: bmNQCyVH
type: multiple-choice
question: What happens to parasite drag if the true airspeed of an aircraft is
multiplied by two, and all other parameters are kept constant? The
parasite drag...
annexes: []
correctOptionId: OP6GADRVM
options:
- id: OVNOQUKEE
text: will be multiplied by two.
why: ""
- id: OIJLIVYXI
text: will be divided by two.
why: ""
- id: OP6GADRVM
text: will be multiplied by four.
why: ""
- id: O6ZKU5GYG
text: is unaffected by speed.
why: ""
explanation: ""
- questionId: ODaWliIo
templateId: QUTWIYQQ7
seed: F43jqWDg
type: multiple-choice
question: "During a turn from base to final, the pilot applies more rudder to
the inside of the turn, skidding the aircraft, to avoid overshooting the
runway. The risk is:"
annexes: []
correctOptionId: OY4R470GH
options:
- id: O23AM8XCL
text: Exceeding the limit load factor.
why: ""
- id: OY4R470GH
text: Spin towards the low wing.
why: ""
- id: OPC9QY2TO
text: Spin towards the high wing.
why: ""
- id: OJ0MUKNMG
text: Over-speeding the aircraft.
why: ""
explanation: ""
- questionId: 8iwLPsRk
templateId: QPCHQJQO
seed: VcJ1Jpkd
type: multiple-choice
question: What is correct regarding Minimum glide angle?
annexes: []
correctOptionId: OSTQEOEJY
options:
- id: OSTQEOEJY
text: Best distance to change in height ratio.
why: ""
- id: OMCQYWI8I
text: Best distance to fuel ratio.
why: ""
- id: OBNCIIBXF
text: Best time to fuel ratio.
why: ""
- id: OODAKSAD1
text: Best time to change in height ratio.
why: ""
explanation: ""
createdAtEpochMs: 1747672273483
startedAtEpochMs: 1747672275126
finishedAtEpochMs: null
href: /modules/atpl/tests/YDJMsHra/study