Calculate the variation with Tt4 of exit Mach number, exit velocity, specific thrust. Fuel/air ratio, and...

Calculate the variation with Tt4 of exit Mach number, exit velocity, specific thrust. Fuel/air ratio, and thrust specific fuel consumption of an ideal turbojet engine for compressor pressure ratios of 10 and 20 at a flight Mach number of 2 and T0= 217K.Perform calculations at Tt4 values of 2400K, 2200K, 2000K and 1800K. Use hPR= 42,800kJ/kg, cp= 1.004kJ/kg and γ= 1.4.

Solutions

Expert Solution

samet mamat answered 1 year ago

Next > < Previous

Related Solutions

Sketch two graphs showing how the specific thrust and thrust-specific fuel consumption (TSFC) of an ideal...

Sketch two graphs showing how the specific thrust and thrust-specific fuel consumption (TSFC) of an ideal hydrogen-burning ramjet varies with flight Mach number from static conditions up to Mach 7 and state why the specific thrust falls to zero when the Mach number approaches 7. Please show working out and describe what is done

The fuel efficiency of an aircraft’s jet engines is described by the thrust-specific fuel consumption (TSFC).

The fuel efficiency of an aircraft’s jet engines is described by the thrust-specific fuel consumption (TSFC). The TSFC measures the rate of fuel consumption (mass of fuel burned per unit time) relative to the thrust (force) that the engine produces. In that manner, even if an engine consumes more fuel per unit time than a second engine, it is not necessarily more inefficient if it also produces more thrust to power the plane. The TSFC for an early hydrogenfueled jet...

Calculate the heat of combustion and the stoichiometric fuel to air ratio (mass and molar) for...

Calculate the heat of combustion and the stoichiometric fuel to air ratio (mass and molar) for 1) Methane and 2) Octane. Comment on whether the assumption of f<<1 is valid for these conditions.

A converging–diverging nozzle is designed to generate an exit Mach number of 2. The nozzle is...

A converging–diverging nozzle is designed to generate an exit Mach number of 2. The nozzle is supplied with air from a large reservoir in which the pressure is kept at 6.5 MPa. Assuming one-dimensional isentropic flow, find a. The maximum back-pressure at which the nozzle will be choked b. The range of back-pressures over which there will be a shock in the nozzle c. The design back-pressure d. The range of back-pressures over which there is supersonic flow on the...

A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle...

A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle is supplied from an air reservoir at 600 kPa and temperature is 300 K. The throat area of the nozzle is 5 cm2 . Determine: (a) The ratio of exit-to-throat area and exit area (b) Given the area ratio in part (a), find the range of back pressure over which the nozzle is choked. What is the critical pressure and design pressure? Also, calculate...

A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle...

A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle is supplied from an air reservoir at 600 kPa and temperature is 300 K. The throat area of the nozzle is 5 cm2. Determine: (a) The ratio of exit-to-throat area and exit area. (b) Given the area ratio in part (a), find the range of back pressure over which the nozzle is choked. What is the critical pressure and design pressure? Also, calculate the...

Calculate air to fuel ratio by mass, for a four-cylinder SI engine running on i) gasoline...

Calculate air to fuel ratio by mass, for a four-cylinder SI engine running on i) gasoline and ii) a mixture of 20% methanol and 80% gasoline both at stoichiometric conditions. Assume gasoline is represented with C8H18 . Calculate any loss of power when gasoline-methanol mixture is used and discuss your results.

how do you relate the air fuel ratio to the equivalence ratio, and the ‘lambda’ ratio

A normal shock wave propagates through stagnant air at 300K and 100kPa with a Mach number...

A normal shock wave propagates through stagnant air at 300K and 100kPa with a Mach number of 1.2. What is the post shock flow velocity in the lab frame of reference and the post shock pressure, and temperature? If a shock wave propagated through helium with the same pressure ratio as the air shock wave, what would its Mach number be?

(a) What is the best air/fuel ratio for an automobile engine? (b) If the mixture is...

(a) What is the best air/fuel ratio for an automobile engine? (b) If the mixture is made leaner, what happens to the hydrocarbon emissions? (c) If the fuel mixture is richer, how does this affect NOx emissions

Subjects