Which of the following is correct?(a) Typically, higher bypass ratio will give higher efficiency(b) Higher bypass ratio always decreases efficiency(c) Lift is equal to weight always(d) Thrust required is the same as thrust availableThis question was posed to me by my college professor while I was bunking the class.My question is from Propulsion in chapter Propulsion of Aircraft Design

Which of the following is correct?(a) Typically, higher bypass ratio w

1.	Which of the following is correct?(a) Typically, higher bypass ratio will give higher efficiency(b) Higher bypass ratio always decreases efficiency(c) Lift is equal to weight always(d) Thrust required is the same as thrust availableThis question was posed to me by my college professor while I was bunking the class.My question is from Propulsion in chapter Propulsion of Aircraft Design
Answer» Right choice is (a) Typically, higher BYPASS ratio will GIVE higher efficiency To explain I would say: We can improve engine efficiency by using high bypass ratio. LIFT is not always same as weight. Lift is same as weight during cruise segment. Thrust required and thrust AVAILABLE are DIFFERENT from each other. Thrust available is actual thrust produced by engine. Thrust required is the amount of thrust required to oppose the drag.

Discussion

No Comment Found

Related InterviewSolutions

An engine has gross thrust of 150KN. If mentioned designed condition needs to be met is that the ram drag should not exceed more than 18KN then, find the net thrust by engine.(a) 132KN(b) 123N(c) 145 N(d) 345MNThis question was addressed to me in homework.The doubt is from Propulsion topic in section Propulsion of Aircraft Design
The installed net propulsive force is defined as _________(a) installed engine thrust minus the drag due to inlet, nozzle and throttle dependent trim drag(b) uninstalled thrust plus drag due to inlet and nozzle(c) installed lift by drag(d) installer wing loadingI have been asked this question in exam.This interesting question is from Propulsion topic in portion Propulsion of Aircraft Design
A piston engine has bhp of 600 at sea level. Now, if engine is operating at an altitude where density ratio is 0.816 then, find the value bhp at that altitude.(a) 37(b) 89(c) 100(d) 289I had been asked this question during an interview.Question is from Propulsion topic in portion Propulsion of Aircraft Design
Turbofan engine uses a large fan at inlet to ________(a) increase efficiency of the engine(b) increase flow velocity(c) increase wing tip lift(d) increase tailplane liftI got this question during an interview for a job.My question is from Propulsion in division Propulsion of Aircraft Design
Engine manufacturer has provided the reference value of inlet pressure recovery as 0.94. If actual pressure recovery is found to be 0.91 then, find the thrust loss. Consider C of 1.25.(a) 0.0375(b) 0.123(c) 0.0865(d) 0.568This question was addressed to me in semester exam.I'm obligated to ask this question of Propulsion topic in portion Propulsion of Aircraft Design
Afterburner is used to ________(a) increase thrust of engine(b) increase fuel efficiency(c) increase lift produced by tail(d) reduce fuel consumptionThis question was posed to me by my school teacher while I was bunking the class.I want to ask this question from Propulsion in section Propulsion of Aircraft Design
The actual available thrust used in performance calculations is termed as __________(a) installed net propulsive force(b) lift to drag ratio(c) installed weight to reference area(d) gross lift and weightThe question was asked by my school teacher while I was bunking the class.I want to ask this question from Propulsion topic in section Propulsion of Aircraft Design
What do you mean by overall pressure ratio?(a) Ratio of pressure at engine exhaust and inlet front face(b) Ratio of dynamic to normal pressure(c) Total pressure divided by stagnation pressure(d) Stagnation pressure divided by dynamic pressureI have been asked this question in a job interview.My doubt is from Propulsion topic in division Propulsion of Aircraft Design
Following diagram represents _________(a) inlet pressure recovery concept(b) lift curve(c) inlet geometry(d) drag polarI had been asked this question in an interview.My doubt stems from Propulsion topic in portion Propulsion of Aircraft Design
An engine has mass flow of 16 unit and bleed mass flow of 0.32 unit. Find the thrust loss due to the bleed air.(a) 4%(b) 6.98%(c) 100.78%(d) 21%The question was asked in a national level competition.My doubt stems from Propulsion topic in division Propulsion of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment