Explanation: Propulsive efficiency is defined as the ratio of obtained thrust power to the energy expanded. Aerodynamic efficiency is defined as lift to drag ratio. Aerodynamic efficiency is primarily consideration of aerodynamic design.

Explanation: Thrust power = thrust*velocity = 150*1000 = 150KW.

Explanation: Net thrust is given by gross thrust minus the ram drag. Drag into velocity will give power not the thrust. This power can be calculated by subtracting the excess power from total available power. Lift to drag ratio is called aerodynamic efficiency of the aircraft.

Explanation: Afterburner is used to increase Thrust produced by the jet engine. It is primarily used by fighter aircraft to increase thrust during takeoff and combat. Afterburning will increase fuel consumption and reduces the fuel efficiency.

= 150-18 = 132KN.

Explanation: Ram drag = Gross Thrust – net Thrust = 12.5 – 0.88*12.5 = 1.5KN.

Explanation: Thrust is nothing but the propulsive force which is used to accelerate aircraft. It will be used to provide forward motion. Thrust depends upon number of factors including mass flow rate, exhaust velocity etc. A typical aircraft thrust is nothing but the change in momentum. And hence, it will be affected by mass flow rate.

Explanation: If required cruise speed is above Mach 2.1 then turbojet engine is suitable among the given options. Piston and reciprocating engine performance is limited to certain speeds. Piston prop engine is limited by tip speed constraints.

Explanation: We can improve engine efficiency by using high bypass ratio. Lift is not always same as weight. Lift is same as weight during cruise segment. Thrust required and thrust available are different from each other. Thrust available is actual thrust produced by engine. Thrust required is the amount of thrust required to oppose the drag.

Explanation: Turbine inlet temperature is one of the biggest obstacle of current engine design. For best Thrust and efficiency it is desirable to use stoichiometric air fuel ratio of 15:1. However, this generated tremendous high temperatures. Such high temperatures are beyond the limits of materials used for Turbine.

Explanation: Overall pressure ratio is defined as ratio of pressure at engine exhaust and inlet front face. The overall pressure ratio or opr is used to measure the ability of an engine to accelerate the exhaust. It has direct impact on thrust and propulsive efficiency of the engine.

Explanation: Uninstalled engine data is available from an engine manufacturer. It can also be found by using preliminary cycle analysis or by using fudge factor approach. Thin airfoil they is used for airfoils with thin profiles. Lifting line theory is an aspect of Aerodynamics.

Explanation: At low subsonic speed, low bypass Turbofan engine should be adopted among the given options. Turboprop has speed limitation due to propeller. Ram jet engine cannot be used at low subsonic speed as ram jet will require assistance to achieve adequate design condition. Ramjet can be used for speeds above Mach 2.8.

Explanation: To Increase efficiency, more specifically propulsive efficiency of the engine a turbofan engine uses a fan. Some air is bypassed around the engine and not being used for combustion. This helps to increase efficiency.

Explanation: A Typical C – D nozzle consists of convergent section as well as divergent section. Apart from those it also includes a throat section at where flow is in sonic condition. Incoming flow initially has subsonic speed which is increased by convergent section. At throat, flow reaches the sonic speed and as it progresses further in the divergent section it further expands to supersonic speeds.