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3. A normal shock wave exists in Mach 2 stream of air having temperature and pressure...
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming...
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming flow stagnation pressure of 200 kPa(abs). In addition to the stagnation pressure downstream of the shock, also give the Mach number and (static) pressure downstream of the shock. DISCUSSION: Compare the "shock compression" (increase in STATIC pressure) obtained from the normal shock to the compression that would be obtained from an isentropic deceleration to the same Mach...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at...
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at a Mach number of 2.5. The pressure and temperature of air are 61.64 kPa and 262.15 K, respectively, upstream of the shock The properties of air are k 1.4 and R = 0.287 kJ/kg K, and the properties of helium arek 1.667 and R 2.0769 kJ/kg-K. [Udara mengalir dengan mantap pada muncung yang mengalami kejutan normal di nombor Mach 2.5. Tekanan dan suhu udara...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, wh...
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, what is the throat pressure and temperature? c. What are the Mach number and speed (m/s) at the throat? I d. If the flow in the nozzle is isentropic, but a normal shock forms at the exit plane, what are the pressure, temperature and Mach number downstream...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming flow stagnation pressure of 200 kPa(abs). In addition to the stagnation pressure downstream of the shock, also give the Mach number and (static) pressure downstream of the shock. DISCUSSION: Compare the "shock compression" (increase in STATIC pressure) obtained from the normal shock to the compression that would be obtained from an isentropic deceleration to the same Mach...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
Question 2 Soalan 2] (a) Air flowing steadily in a nozzle experiences a normal shock at a Mach number of 2.5. The pressure and temperature of air are 61.64 kPa and 262.15 K, respectively, upstream of the shock The properties of air are k 1.4 and R = 0.287 kJ/kg K, and the properties of helium arek 1.667 and R 2.0769 kJ/kg-K. [Udara mengalir dengan mantap pada muncung yang mengalami kejutan normal di nombor Mach 2.5. Tekanan dan suhu udara...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, what is the throat pressure and temperature? c. What are the Mach number and speed (m/s) at the throat? I d. If the flow in the nozzle is isentropic, but a normal shock forms at the exit plane, what are the pressure, temperature and Mach number downstream...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
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