Aircraft Design MCQ – Propulsion – Jet-Engine Integration-1
1 - Question
What do you mean by scale factor in terms of rubber engine?
a) ratio of thrust required by rubber engine to the actual thrust from selected existing engine
b) Lift to drag ratio
c) Thrust coefficient to drag coefficient
d) Thrust required to thrust available
Explanation: For a typical rubber engine, scale factor is defined as ratio of thrust required by rubber engine to the actual thrust from selected existing engine. Scale factor can vary based on our requirements. Lift to drag ratio is primarily concern of aerodynamics of aircraft.
2 - Question
Which of the following is correct?
a) Length L = Lactual*(SF) 0.4
b) Length L = Lactual / (SF) 0.4
c) Length L = Lactual*(SF) 2
d) Length L = 2*Lactual
Explanation: If our chosen existing engine has length of Length of Lactual then, the length of rubber engine is given by, Length L = Lactual*(SF)0.4. SF stands for scale factor.
3 - Question
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 unit
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.
4 - Question
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 in
Explanation: 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.
5 - Question
Evaluate required scale factor if ratio of weight of the rubber engine and the actual selected engine is 0.8.
Explanation: Given, ratio of rubber engine weight (w) and actual engine weight (W) = 0.8 Now, weight of the rubber engine is given by, w = W * SF1.1 Hence, SF1.1 = w/W = 0.8 1.1*ln (SF) = ln0.8 = -0.223 Hence, ln (SF) = -0.223/1.1 = -0.2028 Hence, SF = e-0.2028 = 0.8164.
6 - Question
Subsonic non after burning engine needs to be design based on following data. Take off trust is 15000 N and bypass ratio is 1.2. Find the weight of this engine. Consider first order statistical jet engine model.
a) 3123 unit
b) 325 unit
c) 445.5 unit
d) 560.59 unit
Explanation: Given, Thrust T = 15000N, BPR = 1.2 Now, weight is given by, W = 0.084 * (T1.1)* e (-0.045*BPR). W = 0.084 * (150001.1) * e (-0.045*1.2) = 0.084*39237.4147*0.9474 = 3123 unit.
7 - Question
Based on first order statistical jet engine model, we have been given a task to design a subsonic non afterburning engine which is operating at maximum Mach number of 0.7. Evaluate the approximate length required to build this engine. Given thrust at takeoff is 9600 unit.
a) 81 unit
b) 10 unit
c) 20 unit
d) 22 unit
Explanation: Given, Thrust = 9600unit, Mach number M = 0.7 Length L = 2.22*T0.4*M0.2 = 2.22*96000.4*0.70.2 = 2.22*39.165*0.9311 = 80.95 ∼ 81 unit.
8 - Question
Engine which can be estimated through statistical jet engine model has bypass ratio of 1.2 and maximum thrust at takeoff is 8000 Newton then what should be the design diameter for this engine. Consider a subsonic non after burning engine.
a) 36.87 unit
b) 6.19 unit
c) 7.2 unit
d) 58.93 unit
Explanation: Given, Thrust = 8000unit, BPR = 1.2 Diameter d is given by, d = 0.393 * (T0.5) * e (0.04 * BPR) = 0.393 * (8000)0.5 * e (0.04 * 1.2) = 0.393*89.442*1.049 = 36.87 unit.
9 - Question
If bypass ratio of subsonic non afterburning engine is 1.5 then, what will be the value of maximum thrust specific fuel consumption.
Explanation: Given, BPR =1.5 Maximum thrust SFC = 0.67*e(-0.12*BPR) = 0.67* e(-0.12*1.5) = 0.556.
10 - Question
Subsonic non afterburning engine has takeoff thrust of 8000 Newton and is operating with BPR of 1.2 then, what will be the approximate value of thrust at cruise.
a) 2001.5 unit
b) 1001.5 unit
c) 500 unit
d) 100 unit
Explanation: Given, Thrust T1 = 8000N, BPR = 1.2 Now, thrust at cruise T = 0.60 * T10.9 * e (0.02*BPR) = 0.60 * (8000)0.9 * e (0.02*1.2) = 0.60*3256.724*1.024 = 2001.49 = 2001.5 unit.
11 - Question
Inlet location will not affect engine performance.
Explanation: Location of an inlet is very important factor in one of the crucial factor affecting engine performance. Inlet location is affected by Wing wake, vortex etc. Hence, as a result of wake and vortex engine can stall. Therefore, inlet location should be adequate
12 - Question
Which of the following is an advantage of nose inlet?
a) Clean airflow
b) Unclean airflow
c) Very long internal duct
d) Swirled flow always
Explanation: 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.
13 - Question
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 AOA
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.
14 - Question
Following diagram represents _____________
a) inlet applicability
b) outlet geometry
c) exhaust section
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.
15 - Question
Large cowl lip radius will produce ____________
a) shock separated flow outside of the inlet
b) shock attached flow
c) high lifting tendency always
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.