Inlet pressure recovery is defined as ______(a) total pressure deliver to the engine divided by freestream total pressure(b) total dynamic pressure(c) incoming velocity by incoming Mach number(d) lift to drag ratioThe question was posed to me in semester exam.This interesting question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design

Inlet pressure recovery is defined as ______(a) total pressure deliver

1.	Inlet pressure recovery is defined as ______(a) total pressure deliver to the engine divided by freestream total pressure(b) total dynamic pressure(c) incoming velocity by incoming Mach number(d) lift to drag ratioThe question was posed to me in semester exam.This interesting question is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Answer» Right CHOICE is (a) total pressure deliver to the engine divided by freestream total pressure The best explanation: Inlet pressure RECOVERY is NOTHING but the total pressure which is deliver to the engine divided by the free stream total pressure. DYNAMIC pressure is exerted due to velocity of the fluid. Lift drag ratio is more important for the aerodynamics of the AIRCRAFT.

Discussion

No Comment Found

Related InterviewSolutions

Calculate the approximate value of length at which supersonic after burning engine could be design in such a way that thrust at takeoff will be 29800 unit and maximum Mach number will be 2.12.(a) 219(b) 100(c) 301(d) 183.129The question was asked by my college director while I was bunking the class.Question is from Propulsion in section Propulsion and Fuel System Integration of Aircraft Design
Following diagram represents __________(a) piston prop(b) turboprop(c) turbojet(d) rocketI got this question during an interview for a job.The question is from Propulsion Selection in section Propulsion and Fuel System Integration of Aircraft Design
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*LactualThe question was posed to me in a national level competition.This key question is from Propulsion in portion Propulsion and Fuel System Integration of Aircraft Design
If bypass ratio of subsonic non afterburning engine is found to be 2.1 then, what will be the specific fuel consumption of the same engine at cruise?(a) 0.8(b) 0.1(c) 0.3(d) 0.4I have been asked this question in semester exam.The query is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
We need to design a supersonic fighter with afterburner which has maximum Mach number of 1.8. If thrust at takeoff is 10000 unit and bypass ratio is 0.71 then, find ratio of length to the diameter for this engine.(a) 4.9(b) 1.8(c) 2(d) 3.4I got this question by my school teacher while I was bunking the class.The doubt is from Propulsion in division Propulsion and Fuel System Integration of Aircraft Design
Following diagram represents ______(a) 2D ramp inlet(b) Conical inlet(c) Pitot inlet(d) Flush inletI have been asked this question in semester exam.Enquiry is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Following diagram represents ______________(a) chin inlet(b) armpit inlet(c) wing tip inlet(d) tail tip inletThe question was posed to me during an interview for a job.I want to ask this question from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design
Which of the following is an incorrect example for BL diverter?(a) Step diverter(b) Boundary layer bypass duct(c) Boundary layer suction(d) FlapThe question was asked in examination.My doubt is from Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design
Following diagram represents _______________(a) wing root inlet(b) armpit inlet(c) chin inlet(d) nose inletI had been asked this question in my homework.My query is from Propulsion topic in division Propulsion and Fuel System Integration of Aircraft Design
Following diagram represents _____(a) updraft cooling(b) downdraft cooling(c) updraft lifting(d) downdraft liftingThis question was posed to me during an interview.I'm obligated to ask this question of Propulsion topic in section Propulsion and Fuel System Integration of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment