In a scramjet engine, the Mach number at the entry of the combustor is2 points00.362

The critical Mach number of an airfoil is attained when2 pointsThe Mach number somewhere on the airfoil is unityThe freestream Mach number is sonicThe freestream Mach number is supersonicThe Mach number everywhere on the airfoil is supersonic

The Mach number is the ratio between:Group of answer choicesThe speed of the fluid and the speed of soundThe speed of a wave to the speed of soundThe speed of a vehicle to the speed of soundAll of the above

A supersonic vehicle powered by a ramjet engine is cruising at a speed of1000 m/s. The ramjet engine burns hydrogen in a subsonic combustor to producethrust. The heat of combustion for hydrogen is 120 MJ/kg. The overall efficiencyof the engineo , defined as the ratio of propulsive power to the total heat releasein the combustor, is 40%. Taking acceleration due to gravity0 10g = m/s2, thespecific impulse of the engine is _____________ seconds.(round off to the nearest integer).

The fluid velocity at the exit of a nozzle is 280 m/s. The velocity is 346 m/s. Determine the Mach number for the flow.Group of answer choices0.2361.2361.8090.809

Air enters a jet engine through section 1 with an area of A1=0.5 m2 at a (relative) speedof 250 m/s. The pressure at the entrance is atmospheric pressure (approximately 105 Pa)and the temperature is 300 K. Inside the engine, the injected fuel mixes perfectly withair, with fuel to air mass ratio of 1:30. The enthalpy and the kinetic energy flow rate ofthe fuel can be neglected at the fuel inlet. The combustion releases a heat per unit mass(of air) of 200 kJ/kg, after which the mixture is expanded through a nozzle to the exitsection 2 whose area is A2= 0.4 m2. The product of combustion can be taken to havethe same properties of air (such as Cp=1.005 kJ/kg k, γ=1.4 and so on). The nozzleperfectly expands the flow such that at the exit 2, the pressure is atmospheric pressure.The temperature of the flow at the exit is 400 K. The figure below shows a roughschematic of the engine and the flow. Find the thrust generated by the engine.