90 + Interview Questions in Propulsion And Fuel System Integration in Aircraft Design Page 2 InterviewSolution

51.	Integral tanks are ___________(a) cavities within the aircraft’s airframe itself(b) external tanks needs to be fabricated(c) external tanks required to put in the airframe(d) there is no such type of fuel tankThis question was addressed to me in an online interview.My question is taken from Fuel System topic in division Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct option is (a) cavities within the aircraft’s airframe itself Easy explanation: As NAME suggests a TYPICAL INTEGRAL tank is an integral part of the aircraft itself. Integral tanks are cavities within the structure of airframe. These cavities are then SEALED in order to FORM a fuel tank. Integral tanks are not external tanks.

Discussion

52.	A turboprop engine is designed to generate bhp of 2500. Estimate the appropriate weight of the engine based on statistical models.(a) 893.84 lb.(b) 21kg(c) 4555lb(d) 321 slugThe question was posed to me in an international level competition.My enquiry is from Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» Right answer is (a) 893.84 lb. Explanation: GIVEN, bhp = 2500 Now, approximate value of WEIGHT is given by, W = 1.67bhp^0.803 = 1.672500^0.803 = 893.84 lb.

Discussion

53.	Which of the following is part of a turbine engine?(a) compressor(b) Flap(c) Aileron(d) ElevatorThe question was posed to me in semester exam.My doubt is from Propulsion Selection topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct OPTION is (a) COMPRESSOR To explain: Compressor is an integral part of TURBINE engine. Flap is secondary control surface. Aileron and elevator are primary control surface. Aileron is USED for rolling MOTION and elevator is used for pitching motion.

Discussion

54.	Which of the following is correct?(a) Compressor consumes work produced by turbine(b) Compressor produces work to drive shaft(c) Compressor increases velocity of the flow(d) Lift is always same as weightThe question was asked at a job interview.My doubt is from Propulsion Selection topic in division Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct answer is (a) Compressor consumes WORK produced by TURBINE To explain I would SAY: Turbine generates work to drive the shaft. This work is consumed to drive compressor. Compressor doesn’t produce work. Lift is not always same as weight. Compressor is used to increase pressure and temperature.

Discussion

55.	____________ is the most common type of boundary layer diverter used for supersonic applications.(a) Channel diverter(b) Empennage(c) Aileron(d) ElevatorThe question was asked during an interview.Enquiry is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct ANSWER is (a) Channel diverter Explanation: Channel diverter is considered as most common type of BOUNDARY layer diverter USED for supersonic applications. It offers high performance among the other types. Empennage is tail section of the aircraft.

Discussion

56.	Following diagram represents _________________(a) typical Podded engine(b) buried engine(c) nose buried engine location(d) side buried engine locationThis question was posed to me by my school principal while I was bunking the class.My question is based upon Propulsion in division Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT answer is (a) TYPICAL Podded engine To elaborate: A typical Podded engine configuration is shown in the above DIAGRAM. Buried engines are located inside aircraft body itself. Nose buried engine and SIDE buried engine are typical EXAMPLE of buried engine arrangements.

Discussion

57.	At exhaust of nozzle temperature is 200k and density of the flow is 1.01 kg/m^3. If back pressure is 1 bar then, nozzle is ______________(a) nozzle can be under or over expanded(b) under expansion(c) over expanded(d) design conditionI got this question in a job interview.My question is based upon Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» Right choice is (c) over EXPANDED The best I can explain: Given, temperature t 200k, DENSITY d 1.01 kg/m^3 Now, EXIT PRESSURE p = dRT = 2002871.01 = 57974 = 0.57 bar < 1 bar Since exit pressure p < back pressure, the nozzle is over expanded.

Discussion

58.	A Turbofan engine is to be scale in order to have our desired engine characteristics. If length of the existing engine selected is 2.5 unit and required scale factor is 0.8 then, evaluate approximate length of our engine.(a) 2.28 unit(b) 5.6 unit(c) 10 unit(d) 15 unitI got this question in a national level competition.The origin of the question is Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct option is (a) 2.28 unit Best explanation: GIVEN, ACTUAL length Lactual = 2.5unit, S.F. = 0.8 Approximate length is given by, Length L = Lactual(SF) ^0.4 Length L = 2.5(0.8) ^0.4 = 2.28 unit.

Discussion

59.	Typically, diffuser length is about eight times the diameter for supersonic application.(a) True(b) FalseThis question was addressed to me in an interview for internship.This interesting question is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct answer is (a) True Best explanation: Diffuser length depends upon the application. Theoretically for supersonic applications, diffuser length should be 8 times the diameter. This is to OPERATE at maximum efficiency. We can use LONGER than diameter as well. However, this will INCREASE DRAG and WEIGHT as well.

Discussion

60.	Following diagram represents ___________(a) preliminary sizing of capture area(b) lift curve(c) drag polar(d) drag coefficient curveThe question was posed to me by my school teacher while I was bunking the class.I would like to ask this question from Propulsion in division Propulsion and Fuel System Integration of Aircraft Design
Answer» Right ANSWER is (a) PRELIMINARY sizing of capture area To elaborate: Preliminary sizing of capture area is SHOWN in the above diagram. It provides typical guidelines and values to get preliminary sizing of capture area. Drag POLAR is used to provide relationship between lift and drag.

Discussion

61.	Following diagram represents __________(a) cd nozzle(b) convergent nozzle(c) divergent nozzle(d) constant area nozzleThe question was posed to me by my school teacher while I was bunking the class.Enquiry is from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct answer is (a) CD nozzle Easy explanation: Above diagram is representing concept of C-D nozzle. Cd nozzle consists of both convergent and divergent SECTION. It is used for ROCKET propulsion where high SPEED is required. Typical cd nozzle consists a throat area. At throat Mach number is 1. Hence at throat flow is in sonic CONDITION. Above diagram is illustrating a typical bell nozzle geometry.

Discussion

62.	Which of the following is an example of a cooling system?(a) Downdraft cooling(b) Downdraft lofting(c) Sideway lofting(d) Sideway circulationI have been asked this question in homework.My question comes from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct choice is (a) Downdraft cooling To explain I would say: Downdraft cooling is a typical example of a cooling system which can be used in aircraft. AIR FLOWS in downward direction in the downdraft cooling CONFIGURATION. Lofting is MATHEMATICAL modelling of skin and aircraft. Circulation is related to vorticity in the flow.

Discussion

63.	Following diagram represents ________________(a) armpit inlet(b) wingtip inlet(c) lift curve(d) tail sectionI have been asked this question during an online exam.I'm obligated to ask this question of Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» The CORRECT choice is (a) armpit INLET For explanation: The above diagram is representing the TYPICAL armpit inlet location. This type of inlet is risky. This can be USED to have short internal duct. Lift curve is curve representing lift VARIATIONS.

Discussion

64.	Find the ratio of weight to length of the turboprop engine which has bhp of 3000.(a) 12.60(b) 60.12(c) 60.012(d) 60.1206I have been asked this question in a national level competition.I'd like to ask this question from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» The CORRECT ANSWER is (a) 12.60 To EXPLAIN: Given, bhp = 3000. Now, ratio of weight to LENGTH is given by, W/L = 0.403(bhp)^0.43 = 0.4033000^0.43 = 12.60.

Discussion

65.	If an aircraft has maximum Mach number of 2 and bypass ratio of 0.71 then, what will be the weight of the engine? (Find the approximate value. Given thrust at takeoff is 10000 Unit.)(a) 1058.5 unit(b) 12000 unit(c) 120(d) 234.585 unitThis question was posed to me during an interview.Asked question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct OPTION is (a) 1058.5 unit For explanation I WOULD say: GIVEN, Mach number M = 2, BPR = 0.71, Thrust T = 10000 unit Now, Weight is given by, W = 0.063T^1.1M^0.25e ^-0.81BPR W = 0.06310000^1.12^0.25e ^-0.810.71 W = 0.06325118.861.189*0.5626 = 1058.5 u

Discussion

66.	Diameter of rubber engine is 94 inch and required scale factor is 0.7 then, what will be the actual diameter of selected engine?(a) 112.35 in(b) 150 in(c) 200 in(d) 50 inThe question was asked in unit test.My query is from Propulsion in division Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT option is (a) 112.35 in The explanation is: Given, DIAMETER d = 94 INCH, S.F. = 0.7 Now, actual diameter is given by, Actual diameter D = d / (SF)^0.5 = 94 / (2.7)^0.5 = 112.35in.

Discussion

67.	Which of the following is an advantage of nose inlet?(a) Clean airflow(b) Unclean airflow(c) Very long internal duct(d) Swirled flow alwaysThe question was posed to me in examination.Asked question is from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct answer is (a) Clean airflow The EXPLANATION is: The NOSE inlet offers clean air FLOW. It was used in some fighters such as MIG 21. This type of inlet requires long internal duct which is one of the DISADVANTAGES of nose inlet. They are typically located at the nose section of an aircraft.

Discussion

68.	Fuel tanks should not be located at wingtip.(a) True(b) FalseI have been asked this question in an interview.Enquiry is from Fuel System in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT option is (a) True Best explanation: If possible, designer should not place fuel tanks at the wingtip. By locating fuel tanks at wingtip, designer increases the possibility of HAZARD due to LIGHTING STRIKE. Also for roll stability we should LOCATE fuel tanks near to roll axis.

Discussion

69.	What is the use of Turbine?(a) Generate work to drive shaft(b) To compress the flow(c) To increase pressure(d) To increase temperatureThis question was addressed to me in an online interview.This is a very interesting question from Propulsion Selection in section Propulsion and Fuel System Integration of Aircraft Design
Answer» Right answer is (a) GENERATE work to drive shaft To explain: TURBINE is an ESSENTIAL component of gas turbine ENGINE. Turbine is used to decrease temperature and pressure of the gas. Combustion products pressure is REDUCED by turbine. Turbine generates work to drive the shaft.

Discussion

70.	If area ratio is 1.110 then, at which mach number flow is flowing?(a) 0.68(b) 1.89(c) 2(d) 0.21This question was addressed to me in an internship interview.This question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT answer is (a) 0.68 To explain: Given, area ratio A/A* = 1.110 Now, as we KNOW, A/A* = (1/M)(1+0.2M2)30.5787 For given problem, we will substitute different VALUES of MACH number from the options. Let’s consider M = 0.68 Hence, for assumed value of Mach number, A/A* = (1/0.68)(1+0.20.68^2)^30.5787 A/A = 0.8510*1.09248^3 = 1.110. The evaluated area ratio is equal to the given area ratio. Hence, correct value of Mach number is 0.68.

Discussion

71.	Chin inlet sufferers from _____________(a) foreign object ingestion problem(b) shorter duct length(c) duct length is shorter than the nose inlet(d) typically good at high AOAThe question was asked in exam.This question is from Propulsion in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct option is (a) FOREIGN object ingestion problem Best explanation: Chin inlet is good at operating higher AOA. They offers advantages SIMILAR to NOSE but required duct length is shorter. One of the disadvantage of this type is foreign object ingestion. This good AFFECT the PERFORMANCE of engine as well.

Discussion

72.	Following diagram represents ___________(a) typical turbo jet(b) turbofan(c) turboprop(d) reciprocatingThis question was addressed to me in examination.Question is from Propulsion Selection in section Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT CHOICE is (a) typical turbo jet For explanation I WOULD say: As shown in figure, a typical Turbojet engine is shown. Here, turbojet engine is operated by AXIAL flow Compressor as shown in the above schematic diagram. As air passes through Compressor, pressure will INCREASE and then it will be directed to combustion and preceding stages.

Discussion

73.	Which of the following will use suction to divert the boundary layer?(a) Boundary layer suction(b) Step diverter(c) Thrust loading(d) Power loading curveThe question was asked by my college professor while I was bunking the class.Query is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT choice is (a) Boundary LAYER suction For explanation I would SAY: Boundary layer suction is one of the type of the boundary layer diverter. Here, the boundary layer air is removed with the help of suction. It doesn’t benefit from the ram impact. Power LOADING is related to propulsion SYSTEM performance.

Discussion

74.	Following diagram represents _____________(a) inlet applicability(b) outlet geometry(c) exhaust section(d) empennageThis question was addressed to me in an interview for job.My question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct OPTION is (a) INLET applicability Best EXPLANATION: Typical inlet application limits based on Mach number is shown in the diagram. Above diagram is ILLUSTRATING the selection criteria. This criteria is presented for different types of inlets based upon DESIGNED Mach values.

Discussion

75.	Which of the following is correct?(a) (Vtip) static = πnd/60 fps(b) (Vtip) static = nd feet(c) (Vtip) static = 2n*d/360 s(d) (Vtip) static = d/60 fsThis question was posed to me in examination.My question is based upon Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» Right OPTION is (a) (Vtip) static = πnd/60 fps Best explanation: CORRECT relation is given by, (Vtip) static = πnd/60 fps Where, n = rpm BASED on engine data d = diameter Units should be observed CAREFULLY and EQUATION should be used accordingly.

Discussion

76.	Which of the following is not an aircraft propulsion system?(a) High lift device(b) Reciprocating engine(c) Piston engine(d) Rocket engineI have been asked this question during an online exam.Enquiry is from Propulsion Selection in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT choice is (a) High lift device To elaborate: High lift devices are not PART of AIRCRAFT propulsion system. High lift device is used to INCREASE lift produced. Flaps are an example of high lift device which are used at takeoff and landing.

Discussion

77.	Which of the following is not the type of an aircraft propulsion?(a) Longerons(b) Air breathing propulsion(c) Non air breathing propulsion(d) Rocket engineThis question was addressed to me by my college professor while I was bunking the class.My enquiry is from Propulsion Selection topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT OPTION is (a) Longerons To EXPLAIN I would say: Longerons are STRUCTURAL elements of an AIRCRAFT. Longerons are heavy structural members that run straight and used to prevent bending.

Discussion

78.	Which of the following is an advantage of the piston prop engine?(a) Cheap and low fuel consumption(b) Highest speed(c) Supersonic speed always(d) Limited performanceI had been asked this question in a job interview.This intriguing question originated from Propulsion Selection in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT choice is (a) CHEAP and LOW fuel consumption To explain I would say: Piston prop engine are widely USED during early era. Piston prop engine PROVIDES cheap and low fuel consumption. Piston prop engine suffers from speed limits.

Discussion

79.	Following diagram represents ___________(a) turbojet engine with centrifugal compressor(b) piston engine(c) piston prop aircraft(d) turboprop designThe question was asked by my college director while I was bunking the class.This intriguing question originated from Propulsion Selection topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct choice is (a) turbojet engine with centrifugal compressor The EXPLANATION is: A typical Turbojet with centrifugal compressor is SHOWN in above schematic DIAGRAM. Centrifugal force is used as WORKING principle to drive this TYPE of compressor. As shown in figure, it consists of combustion chamber and turbine stage as well.

Discussion

80.	Following diagram represents ___________(a) typical speed limit chart of propulsion system(b) drag polar(c) lift curve slope(d) lift coefficient variationI have been asked this question in an international level competition.My enquiry is from Propulsion Selection topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct option is (a) typical speed limit chart of PROPULSION system To explain I would say: Above diagram is used to show the typical speed limit chart of current propulsion system in aviation. As shown TURBOPROP and piston PROP cannot be used for speeds beyond Mach 1. Lift curve SLOPE is defined as change in lift coefficient per change in angle of attack.

Discussion

81.	At which diameter we should design a supersonic after burning engine for a fighter which will have thrust at takeoff 150000 Unit and bypass ratio of 0.7.(a) 114.67 unit(b) 160.78 unit(c) 350.39 unit(d) 235.78 unitThe question was asked by my school teacher while I was bunking the class.Query is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» Right CHOICE is (a) 114.67 unit The explanation is: Given, THRUST T = 150000 unit, BPR = 0.7. Now, DIAMETER D is given by, D = 0.288T^0.5E ^0.04BPR = 0.288150000^0.5e^0.040.7 Hence, D = 0.288387.31.028 = 114.67 unit.

Discussion

82.	Fuel system includes ____________(a) fuel tanks, fuel lines, fuel pump, etc(b) elevator(c) rudder(d) high lift deviceThe question was posed to me during an internship interview.My question is from Fuel System topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT option is (a) fuel tanks, fuel lines, fuel pump, etc Explanation: Fuel system includes fuel tanks, fuel lines, supply lines, pump, etc. Elevator and rudder are known as PRIMARY control surface. Elevator is used for pitch up and pitch down. Rudder provides YAW MOTION. High lift device is used to INCREASE the amount of lift.

Discussion

83.	Performance of engine can be controlled by nozzle.(a) True(b) FalseI got this question in examination.I would like to ask this question from Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct option is (a) True For explanation: VELOCITY of EXHAUST can be altered by using nozzle. Nozzle expands exhaust FLOW. This will reduce pressure and temperature of the flow. By altering the SHAPE of Nozzle we can ALTER the velocity and performance parameters.

Discussion

84.	Our designed Mach number is 0.8. Find the required area ratio for the design. Assume isentropic relation is valid.(a) 1.038(b) 3.45(c) 5.64(d) 0.12This question was addressed to me during an interview.My question comes from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct OPTION is (a) 1.038 For EXPLANATION: Given, Mach NUMBER M=0.8 Now, area ratio is given by, A/A* = (1/M)(1+0.2M^2)^30.5787 = (1/0.8)(1+0.20.8^2)^30.5787 A/A = 0.7233*1.128^3 = 1.038.

Discussion

85.	Following diagram represents __________(a) typical central fuel tank location(b) rip tank location(c) tip tank at tail(d) tail fuel tankI had been asked this question in homework.I'm obligated to ask this question of Fuel System topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct option is (a) typical central fuel tank location The best explanation: Typical fuel tank is SHOWN in the DIAGRAM. As shown in the diagram Fuel tank is located at the centre and HENCE it is a typical central fuel tank. TIP tank will be located at the tip of wing typically.

Discussion

86.	Following diagram represents ___________(a) turboprop(b) rocket(c) ramjet(d) scramjetThis question was posed to me during an interview for a job.This interesting question is from Propulsion Selection in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» Correct option is (a) turboprop The explanation is: A turboprop is different from traditional PISTON PROP engine. Here, PROPELLER is connected to TURBINE engine via gear box. Rocket is type of AIRCRAFT and spacecraft propulsion system.

Discussion

87.	Large cowl lip radius will produce ____________(a) shock separated flow outside of the inlet(b) shock attached flow(c) high lifting tendency always(d) expansion fanI got this question in class test.My enquiry is from Propulsion in division Propulsion and Fuel System Integration of Aircraft Design
Answer» CORRECT option is (a) shock separated flow outside of the inlet For explanation: Engine performance is influenced by cowl LIP radius. A large cowl lip radius will produce shock separated flow on the outside of an inlet. Large cowl lip will REDUCE distortions. This is very HELPFUL at higher AOA.

Discussion

88.	Following diagram represents ______(a) Conical inlet(b) Spiral inlet(c) NACA flush mount(d) Pitot inletThis question was addressed to me during an online interview.This interesting question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» Right choice is (a) Conical inlet Easiest explanation: The above DIAGRAM is showing a TYPICAL conic or conical inlet geometry. Conical inlet is also known as spike inlet or round inlet. This TYPE of inlets are used to operate in supersonic speeds. The spike inlet is typically lighter but can EXPERIENCE higher cowl drag.

Discussion

89.	What is the function of a typical nozzle?(a) To expand exhaust flow(b) To reduce flow velocity(c) To generate lift to fly(d) To increase pressureThis question was addressed to me in exam.Question is from Propulsion in chapter Propulsion and Fuel System Integration of Aircraft Design
Answer» Right answer is (a) To expand exhaust FLOW Best explanation: FUNCTION of nozzle is to expand flow. Nozzle is used to increase flow VELOCITY by decreasing pressure and temperature of the flow. Lift is generated by WINGS primarily. Pressure can be increased by using compressor.

Discussion

90.	Which of the following is correct for two blade propeller?(a) Diameter d = 22(Hp)^0.25(b) Diameter d = 22(Hp)^0.56(c) Diameter d = 12.22*(Hp)^0.25(d) Diameter d = 2.2 ftThe question was posed to me in final exam.My query is from Propulsion in section Propulsion and Fuel System Integration of Aircraft Design
Answer» The correct option is (a) DIAMETER d = 22(Hp)^0.25 Explanation: An initial estimation of propeller diameter is GIVEN by, Diameter d = 22(Hp)^0.25. Where, Hp is horse power. Above equation provides APPROXIMATE VALUE for 2 bladed propeller diameter.

Discussion

Explore topic-wise InterviewSolutions in .

Which of the following is part of a turbine engine?(a) compressor(b) Flap(c) Aileron(d) ElevatorThe question was posed to me in semester exam.My doubt is from Propulsion Selection topic in chapter Propulsion and Fuel System Integration of Aircraft Design

____________ is the most common type of boundary layer diverter used for supersonic applications.(a) Channel diverter(b) Empennage(c) Aileron(d) ElevatorThe question was asked during an interview.Enquiry is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design

Typically, diffuser length is about eight times the diameter for supersonic application.(a) True(b) FalseThis question was addressed to me in an interview for internship.This interesting question is from Propulsion topic in chapter Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents __________(a) cd nozzle(b) convergent nozzle(c) divergent nozzle(d) constant area nozzleThe question was posed to me by my school teacher while I was bunking the class.Enquiry is from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design

Which of the following is an example of a cooling system?(a) Downdraft cooling(b) Downdraft lofting(c) Sideway lofting(d) Sideway circulationI have been asked this question in homework.My question comes from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents ________________(a) armpit inlet(b) wingtip inlet(c) lift curve(d) tail sectionI have been asked this question during an online exam.I'm obligated to ask this question of Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design

Which of the following is an advantage of nose inlet?(a) Clean airflow(b) Unclean airflow(c) Very long internal duct(d) Swirled flow alwaysThe question was posed to me in examination.Asked question is from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design

Fuel tanks should not be located at wingtip.(a) True(b) FalseI have been asked this question in an interview.Enquiry is from Fuel System in chapter Propulsion and Fuel System Integration of Aircraft Design

If area ratio is 1.110 then, at which mach number flow is flowing?(a) 0.68(b) 1.89(c) 2(d) 0.21This question was addressed to me in an internship interview.This question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents ___________(a) typical turbo jet(b) turbofan(c) turboprop(d) reciprocatingThis question was addressed to me in examination.Question is from Propulsion Selection in section Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents _____________(a) inlet applicability(b) outlet geometry(c) exhaust section(d) empennageThis question was addressed to me in an interview for job.My question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design

Which of the following is not an aircraft propulsion system?(a) High lift device(b) Reciprocating engine(c) Piston engine(d) Rocket engineI have been asked this question during an online exam.Enquiry is from Propulsion Selection in portion Propulsion and Fuel System Integration of Aircraft Design

Fuel system includes ____________(a) fuel tanks, fuel lines, fuel pump, etc(b) elevator(c) rudder(d) high lift deviceThe question was posed to me during an internship interview.My question is from Fuel System topic in portion Propulsion and Fuel System Integration of Aircraft Design

Performance of engine can be controlled by nozzle.(a) True(b) FalseI got this question in examination.I would like to ask this question from Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents ___________(a) turboprop(b) rocket(c) ramjet(d) scramjetThis question was posed to me during an interview for a job.This interesting question is from Propulsion Selection in portion Propulsion and Fuel System Integration of Aircraft Design

Large cowl lip radius will produce ____________(a) shock separated flow outside of the inlet(b) shock attached flow(c) high lifting tendency always(d) expansion fanI got this question in class test.My enquiry is from Propulsion in division Propulsion and Fuel System Integration of Aircraft Design

Following diagram represents ______(a) Conical inlet(b) Spiral inlet(c) NACA flush mount(d) Pitot inletThis question was addressed to me during an online interview.This interesting question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design

What is the function of a typical nozzle?(a) To expand exhaust flow(b) To reduce flow velocity(c) To generate lift to fly(d) To increase pressureThis question was addressed to me in exam.Question is from Propulsion in chapter Propulsion and Fuel System Integration of Aircraft Design