Bissoy.com
Doctors Medicines MCQs Q&A

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.

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. Correct Answer 114.67 unit

Given, Thrust T = 150000 unit, BPR = 0.7. Now, Diameter D is given by, D = 0.288*T0.5*e 0.04*BPR = 0.288*1500000.5*e0.04*0.7 Hence, D = 0.288*387.3*1.028 = 114.67 unit.

Related Questions

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.
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.
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.
Consider the following statements in connection with thrust bearings: 1) Cylindrical thrust bearings have higher coefficient of friction than ball thrust bearings. 2) Taper rollers cannot be employed for thrust bearings. 3) Double-row thrust ball bearing is not possible 4) Lower race, outer race and retainer are readily separable in thrust bearings. Which of the above statements are correct?
Mr. jaman is insured completely for Tk. 150000 of damages to his machinaery . For any damage over Tk. 150000, the insurance company will payTk. 150000 plus only 15% of the additional amount For a recent accident. Mr. jaman was paid Tk. 156000 by the insurance company. What was the total amount of the damage estimated/
The admission ticket for an Art Gallery bears a password which is changed after every clock hour based on set of words Chosen for each day. The following is an illustration of the code and steps of rearrangement for subsequent clock hours. The Time is 9 a.m. to 3 p.m. Day’s first password: First Batch – 9 a.m. to 10 a.m. is not ready cloth simple harmony burning Second Batch – 10 a.m. to 11 a.m. ready not is cloth burning harmony simple Third Batch – 11 a.m. to 12 noon cloth is not ready simple harmony burning Fourth Batch – 12 noon to 1 p.m. not is cloth ready burning harmony simple Fifth Batch – 1 p.m. to 2 p.m. ready cloth is not simple harmony burning and so on. If the password for 11 a.m. to 12 noon was –“soap shy miss pen yet the she”, what was the password for the First Batch?
The admission ticket for an exhibition bears a password which is changed after every clock hour based on set of words chosen for each day. The following is an illustration of the code and steps of rearrangement for subsequent clock hours. The time is 9 a.m. to 3 p.m. Day's first password : First Batch ----- 9 a.m. to 10 a.m. is not ready cloth simple harmony burning Second Batch ----- 10 a.m. to 11 a.m. ready not is cloth burning harmony simple Third Batch ----- 11 a.m. to 12 noon cloth is not ready simple harmony burning Fourth Batch ----- 12 noon to 1 p.m. not is cloth ready burning harmony simple Fifth Batch ----- 1 p.m. to 2 p.m. ready cloth is not simple harmony burning and so on. If the password for 11 a.m. to 12 noon was --- "soap shy miss pen yet the she", what was the password for the first batch ?
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.
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.)
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.