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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?
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?
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.
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.
An aircraft has to be designed to operate at aerodynamic efficiency of 10 at cruise. Find the required thrust to weight ratio for maintaining this unaccelerated steady level flight.
An aircraft is in sustained turn with thrust loading of 0.8 and aerodynamic efficiency of 6. Determine the approximate value of maximum load factor.
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.
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?
A typical jet airliner has cruise thrust to weight ratio of 0.5. Determine at which aerodynamic efficiency this airliner is flying.
Determine the corrections or otherwise of the following assertion and reason : Assertion : Aerobatic prop aircraft has much higher power loading. Reason: Power loading of prop aircraft is ratio of power to the weight of the aircraft. and are true and is the correct reason for b) Both and are true but is not the correct reason for c) Both and are false d) is false but is true