Question

In: Mechanical Engineering

A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for...

A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for the atmospheric conditions (pressure and temperature) at 15 km altitude in the test section of a supersonic wind tunnel. The diameter of the test section is 10 cm. Assume the gas has Y(gamma) = 1.4 and R = 2.077 kJ/kg*K, determine (a) the mass flow rate that must be provided, (b) the nozzle throat area, (c) the reservoir temperature and (d) the reservoir pressure.

Solutions

Expert Solution

samet mamat answered 2 years ago
Next > < Previous

Related Solutions

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...
Consider a Kantrowitz-Donaldson diffuser designed for a flight Mach number of 1.8. The entrance area equals...
Consider a Kantrowitz-Donaldson diffuser designed for a flight Mach number of 1.8. The entrance area equals 3.0 ft2and the ambient airtemperature and pressure are 500R and 0.8atmosphere. The flow is isentropic everywhere except across the normal shockwave. Determine:(a) the minimum cross-sectional area of the throat such that a normal shock may be stabilized at the entrance, (b) the maximum mass flow, and(c) the maximum stagnation pressure possible at the end of the diffuser (with subsonic flow only in the divergent...
FLUID MECHANICS An aircraft flying at an altitude of 5 km with a Mach number of...
FLUID MECHANICS An aircraft flying at an altitude of 5 km with a Mach number of 0.15. Calculate the velocity of the aircraft? (+1 point) Calculate the pitot tube measurement reading at the nose using Bernoulli (+1 point) and Isentropic equations (+1 point) separately. Compare them!!! Calculate pressure coefficient (Cp) at the nose(stagnation) point. (+0.5 point) Calculate the pressure coefficient (Cp) at the point where Mach number reaches 0.25 (+1 point)
A nozzle is is designed to achieve M=4 under expanded exit flow conditions. For the given...
A nozzle is is designed to achieve M=4 under expanded exit flow conditions. For the given total pressure and total temperature, calcuate: a) exit Mach b)mach at which normal shock occurs in the model
A factory has in it five machines, A, B, C, D, and E that produce Smart...
A factory has in it five machines, A, B, C, D, and E that produce Smart Pencils. Machine A produces 5 % of the factory's output with a 2 % defective rate. Machine B produces 10 % of the factory's output with a 3 % defective rate. Machine C produces 25 % of the factory's output with a 4 % defective rate. Machine D produces 3 0% of the factory's output with a 5 % defective rate. Machine E produces...
the southwest flight accident was a being 737 equipped with two engines. it was designed with...
the southwest flight accident was a being 737 equipped with two engines. it was designed with full redundancy for landing purpose, (it can land with only one working engine). Assuming that the engine has a failure rate of 0.0001 per hour and the average flight time is 2 hours a) what are the system reliability and the equivalent system failure rate as far as landing is concerned( assuming no other failure is possible)? b) Assuming that in average every 6...
An ideal turbofan operates at 11,000m with a free-stream Mach number of 0.85. Considering the following...
An ideal turbofan operates at 11,000m with a free-stream Mach number of 0.85. Considering the following design inputs: Bypass ratio:?= 8 Fan pressure ratio:?F= 1.6 Compressor pressure ratio:?c= 25 Fuel heating energy:hPR= 43,500kJ/kg Total temperature downstream of the combustor:Tt4= 1420K a)Calculate all the points and plot the thermodynamic cycle of the core flow on a T-sdiagram. b)Calculate specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency. c)Compare the performance parameters in part b)with those of an ideal...
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?
ADVERTISEMENT
Subjects
ADVERTISEMENT
Latest Questions
ADVERTISEMENT