How to Score High in Pak Navy Weapon Engineering MCQs Test?
If you’re aiming to join the Pak Navy through the Short Service Commission and want to secure a high score in the initial tests to get a merit seat, you’re in the right place. The Pak Navy Weapon Engineering MCQs offer a valuable opportunity for candidates to practice and refine their knowledge before sitting for the competitive exams.
By taking part in these free online practice tests, interested candidates can get familiar with the types of questions that will appear in the tests and boost their chances of making it through the ISSB. Whether you’re aiming for a position in the weapon engineering department or another branch, mastering the MCQs is a key step in your journey to becoming a part of Pakistanโs prestigious Naval force and Naval forces of the world.
How to Excel in Pak Navy Initial Tests: Practice with Weapon Engineering MCQs
Q: The subsequent step after the requirements in conceptual design phase is _____
(a) design take-off gross weight
(b) control
(c) stability
(d) lofting
Answer: (a) design take-off gross weight
Q: The โDesign take-off gross weightโ and โmaximum take-off weightโ are always interchangeable.
(a) True
(b) False
Answer: (b) False
Q: Design take-off gross weight includes ______
(a) only fuel weight
(b) only crew weight
(c) only payload weight
(d) crew, payload and fuel weights
Answer: (d) crew, payload and fuel weights
Q: Avionics systems are an example of ____ weight.
(a) empty
(b) crew
(c) passenger
(d) payload
Answer: (d) payload
Q: Take-off gross weight of an aircraft is summation of _____
(a) empty and payload weight
(b) fuel, payload, crew, empty and miscellaneous weight
(c) fuel and crew weight
(d) only passenger and crew weight
Answer: (b) fuel, payload, crew, empty and miscellaneous weight
Q: In general, the fuel weight is represented by a fraction of total take-off weight.
(a) True
(b) False
Answer: (a) True
Q: A general aviation aircraft is flying with crew load of 115lb, payload of 220lb and fuel weight of 100lb. Find out the design take-off gross weight of the aircraft, given 95lb empty weight.
(a) 435lb
(b) 241lb
(c) 530lb
(d) 500lb
Answer: (c) 530lb
Q: A jet airliner aircraft is flying with crew load of 150kg, payload of 520lb and fuel weight of 500lb. Find out the empty weight if design take-off gross weight of the aircraft is given 1525lb.
(a) 79kg
(b) 79lb
(c) 170lb
(d) 355lb
Answer: (d) 355lb
Q: Cessna 172R has total gross weight of the 1110.98kg with fuel capacity of 210 kg and weight of crew and passenger is 125kg. Find out empty weight fraction.
(a) 775.98kg
(b) 69.84kg
(c) 0.6984
(d) 0.6984lb
Answer: (c) 0.6984
Q: A Jet transport aircraft is flying with crew load of 175kg, payload of 1400kg and fuel weight of 500kg. Find out Fuel to empty weight fraction, if design take-off gross weight of the aircraft is 5600lb.
(a) 0.1831
(b) 1.076
(c) 0.196
(d) 0.1418
Answer: (c) 0.196
Q: Wing and airfoil both are 3D phenomena.
(a) True
(b) False
Answer: (a) True
Q: A 3D airfoil is called _____________
(a) engine
(b) airfoil
(c) wing
(d) lofting
Answer: (c) wing
Q: If taper ratio is T and span is b with surface area as S then the root chord is _____
(a) Croot = 2S / (b(3+T))
(b) Croot = 2S / (b(1+T))
(c) Croot = 2S / (2b(1+T))
(d) Croot = 2S / (1+T)
**Answer: (b) Croot = 2S / (b*(1+T))**
Q: A wing has root chord of 2m and taper ratio of 0.5. Determine what will be the value of tip chord?
(a) 1.5
(b) 1.5m
(c) 1
(d) 1m
Answer: (d) 1m
Q: Wing planform is affected by _____
(a) sweep only
(b) aspect ratio, sweep angle, taper ratio
(c) aspect ratio only
(d) taper ratio only
Answer: (b) aspect ratio, sweep angle, taper ratio
Q: Wing aspect ratio is defined as _____
(a) span square plus reference area
(b) span square multiplied by reference area
(c) span square divided by reference area
(d) span square
Answer: (c) span square divided by reference area
Q: A typical wing has aspect ratio of 7 and span of 2m. If taper ratio T = 0.2 then, find the value of root chord.
(a) 0.4761m
(b) 0.61m
(c) 0.81m
(d) 0.71cm
Answer: (b) 0.61m
Q: If a sailplane is to be designed then, the aspect ratio of the sailplane will be ______
(a) same as military aircraft
(b) higher than military aircraft
(c) lower than military aircraft
(d) exactly half of the military aircraft
Answer: (b) higher than military aircraft
Q: A jet fighter is operating at Mach number of 1.4. Wing chord is 1m then, find the location of aerodynamic centre.
(a) 0.8m
(b) 0.4
(c) 0.4m
(d) 0.8
Answer: (c) 0.4m
Q: Which of the following is correct?
(a) Lofting is a conceptual design of wing
(b) Military aircraft have much higher aspect ratio
(c) Civil aircraft are flying at hypersonic speed
(d) Weight will be more for higher aspect ratio wing
Answer: (a) Lofting is a conceptual design of wing
Q: Which type of wing planform is shown below?
Find the type of wing planform shown in the given diagram
(a) Tapered wing
(b) Elliptic wing
(c) Rectangular wing
(d) Delta wing
Answer: (d) Delta wing
Q: Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: Taper ratio will affect the weight of wing.
Reason [R]: For finite taper ratio, wing thickness will be different at root and tip.
(a) Both [A] and [R] are true and [R] is the correct reason for [A]
(b) Both [A] and [R] are true but [R] is not the correct reason for [A]
(c) [A] is true but [R] is false
(d) [A] is false but [R] is true
Answer: (a) Both [A] and [R] are true and [R] is the correct reason for [A]
Q: A twin turboprop engine is flying with 120m/s. Wing of the aircraft has span of 2m and lift co-efficient as 0.15 with aspect ratio as 9.2. Find the lift produced by the wing.
(a) 574.18
(b) 574.18 N
(c) 120 N
(d) 620 N
Answer: (b) 574.18 N
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