Air from a reservoir at 59 ◦ F flows isentropically through a convergingdiverging duct and forms...
Air from a reservoir at 59 ◦ F flows isentropically through a convergingdiverging duct and forms a normal shock downstream of the throat. The temperature increases by a factor of 2 across the shock. Compute the velocity upstream and downstream of the shock in BG units.
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Air from a reservoir at 59 ◦ F flows isentropically through a
convergingdiverging duct and forms...
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...
Air in a large storage tank is 91 psia and 60°F is flowing isentropically through the...
Air in a large storage tank is 91 psia and 60°F is flowing isentropically through the duct shown below to the atmosphere. The pressure, psia, in the duct throat is most nearly Po = 91 psia مها : 7 Pater Hint: Assume the flow is choked, then the fluid speed in the throat is equal to the speed of sound and the pressure in the throat is equal to the critical pressure p
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section...
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section of the nozzle. The areas at throat, section 1. and section 2 are given in the figure below The sections 1 and 2 are located immediately upstream and downstream of the normal respectively. Therefore, the sections 1 and 2 are assumed to have the same area. There temperature and pressure are given as 300 K and 110 kPa, respectively. The entire isentropic except for...
Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig. 3.4, where there is a normal shock wave. Compute (a) Pi (b) P2 (c) Po2 (d) A 2 (e) Po3 (f)A* (g) P3 (h) To...
Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig. 3.4, where there is a normal shock wave. Compute (a) Pi (b) P2 (c) Po2 (d) A 2 (e) Po3 (f)A* (g) P3 (h) To3 Air Reservoir Po 300 kPa 12 13 T01-500 K | Shock P100 psia
Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig....
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging...
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging nozzle with throat area of 1 em and exit area of 2.7 cm2 When the mass flow is 0.05 kg/s, pitot tube reads py 250.6 kPa and 240 kPa at the exit plane. (a) (15 pt.) Is there a normal shock wave in the duct? Justify your answer. If so, compute the Mach number just downstream of the shock (b) (10 pt.) Compute the...
if you sure then solve. will be rate Air flows at 0.05 kg/s through n insulated circular duct such that the (gauge)...
if you sure then solve. will be rate
Air flows at 0.05 kg/s through n insulated circular duct such that the (gauge) pressure immediately downstream of a blower is 10 kPa You may neglect the impact of elevation change in your analysis. Part A the air that would be expected between upstream and downstream locations. If the pressure at a downstream location within the duct is measured as 8 kPa, estimate the change the temperature Express your answer to three...
30 points Air flows from a tank through a nozzle and it is discharged into a...
30 points Air flows from a tank through a nozzle and it is discharged into a standard atmosphere, as shown in the Figure. A normal shock stands in the exit of the nozzle, with an area of Ae-12cm2 and an Mach number of Me-2 just before the normal shock. Air velocity is neglected in the large tank with an air temperature of 100°C. Determine: 3. a) b) The area and the temperature at the throat The pressure before the normal...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
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...
Air in a large storage tank is 91 psia and 60°F is flowing isentropically through the duct shown below to the atmosphere. The pressure, psia, in the duct throat is most nearly Po = 91 psia مها : 7 Pater Hint: Assume the flow is choked, then the fluid speed in the throat is equal to the speed of sound and the pressure in the throat is equal to the critical pressure p
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section of the nozzle. The areas at throat, section 1. and section 2 are given in the figure below The sections 1 and 2 are located immediately upstream and downstream of the normal respectively. Therefore, the sections 1 and 2 are assumed to have the same area. There temperature and pressure are given as 300 K and 110 kPa, respectively. The entire isentropic except for...
Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig. 3.4, where there is a normal shock wave. Compute (a) Pi (b) P2 (c) Po2 (d) A 2 (e) Po3 (f)A* (g) P3 (h) To3 Air Reservoir Po 300 kPa 12 13 T01-500 K | Shock P100 psia
Air flows from a reservoir where P 300 kPa and T 500 K through a throat to section 1 in Fig....
Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging nozzle with throat area of 1 em and exit area of 2.7 cm2 When the mass flow is 0.05 kg/s, pitot tube reads py 250.6 kPa and 240 kPa at the exit plane. (a) (15 pt.) Is there a normal shock wave in the duct? Justify your answer. If so, compute the Mach number just downstream of the shock (b) (10 pt.) Compute the...
if you sure then solve. will be rate
Air flows at 0.05 kg/s through n insulated circular duct such that the (gauge) pressure immediately downstream of a blower is 10 kPa You may neglect the impact of elevation change in your analysis. Part A the air that would be expected between upstream and downstream locations. If the pressure at a downstream location within the duct is measured as 8 kPa, estimate the change the temperature Express your answer to three...
30 points Air flows from a tank through a nozzle and it is discharged into a standard atmosphere, as shown in the Figure. A normal shock stands in the exit of the nozzle, with an area of Ae-12cm2 and an Mach number of Me-2 just before the normal shock. Air velocity is neglected in the large tank with an air temperature of 100°C. Determine: 3. a) b) The area and the temperature at the throat The pressure before the normal...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
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