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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.
Consider the following statements 1. Value of transient stability limit will be lower than steady-state stability limit 2. Transient stability limit is the maximum flow of power through a particular point in the power system without loss of stability when large and sudden disturbances occur 3. Critical clearing angle is related to the steady-state stability limit Which of the above statement(s) is/are correct?
Fixed engine sizing method is adopted for aircraft. If thrust per engine is 20000 unit and thrust loading T.L. is 0.8 then, find the take-off gross weight. Given aircraft has 2 engines.
Let’s consider our aircraft has to generate thrust of 150KN during cruise. If at the cruise thrust loading is 0.86 then, at which value of Lift our aircraft is flying?
We can design our aircraft to cruise for 3 different lift to drag ratio. Lift to drag ratio are as follows: 10, 12 and 11.25. Now, if we want to reduce thrust required to fly then, at which value of lift to drag ratio our aircraft needs to be designed so that it can operate with minimum thrust required?
Which of the following statements are correct for turbo-prop powered aircraft? 1. The propulsion efficiency of turboprop is higher than that of turbo-jet and rockets for low speeds up to about 800 km/hr. 2. For the same thrust the turbine in the turbo-prop aircraft is smaller than in the turbo-jet aircraft 3. For the turbo-prop the flight velocity cannot exceed the jet velocity.
An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft thrust is 46082.75N then determine aircraft drag.
An A/C is flying with thrust loading at take-off is 0.9. If thrust at take-off and cruse is equal then, determine the thrust loading during cruise.
Find the acceptable value of ram drag if Turbojet is designed to provide net thrust of 88% of gross thrust. Engine gross thrust is 12.5KN.