Bissoy.com
Doctors Medicines MCQs Q&A

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.

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. Correct Answer 4.9

Given, Mach number M = 1.8, thrust T = 10000 unit, BPR = 0.71. Now, Ratio of length to diameter is given by, L/D = 10.625*T-0.1*M0.2*e 0.04*BPR = 10.625*10000-0.1*1.80.2*e 0.04*0.71 Hence, L/D = 10.625*0.3981*1.1247*1.028 = 4.9.

Related Questions

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.
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.)
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.
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.
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.
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?
Rocket A has twice the pressure thrust of rocket B while it has half the momentum thrust as that of B. If the momentum thrust of B is 5 times its pressure thrust, find the ratio of total thrust of A to B.
A jet fighter aircraft is flying with maximum Mach number of 2.0. What will be the thrust loading of the fighter?
Across the normal shockwave: 1) Stagnation pressure decreases whereas stagnation temperature remains constant 2) Mach number before the shockwave is always greater than one and after the shockwave, the Mach number need not be less than one 3) Across the shockwave there is a rise in pressure and temperature 4) The product of Mach number downstream of normal shockwave and upstream of normal shockwaves always one Which of the above statements are correct?
As a designer let’s consider that we want to build an aircraft weighing 28000 units at take-off. How many engine will require if our thrust loading T.L. is 0.71 and thrust per engine is 10000 unit?