please write your own answer! 3. Air flows in a converging-diverging nozzle is operating between the second and the thi...
please write your own answer! 3. Air flows in a converging-diverging nozzle is operating between the second and the third critical points as shown in figure below 40° IS where M, 2.35, T = 160K, p, = 0.7 bar and the receiver pressure is 1.0 bar (a) Compute the Mach number, temperature and the flow deflection in region 2 5 (b) Through which angle is the flow deflected as it passes though the next shock eave? (c)Determine the conditions in...
ANSWER [0.54 and 1.63] (b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K. (b) Air flows through a converging-diverging...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
UBAV Air flows through a converging-diverging nozzle diffuser. A normal shock stands in the diverging section of the nozzle. Assuming isentropie flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system. Solve wsing equations rather than with the tables Note: The Specific heat ratio and gas constant for air are given as k-1 and R 0.287 kJ/kg-K respectively Give Values Inlet Temperature: TI(K)-340 Inlet pressure: P1 (kPa) - 550 Inlet Velocity:...
Air, at po = 160 lbf/in2 and To = 300°F, flows isentropically through a converging-diverging nozzle. At section 1, where A1 = 288 in2, the velocity is V1 = 2068 ft/s. Calculate the inlet Mach number (Ma1) and the throat area (A*). The inlet Mach number is-------- . The throat area is---------- ft2.es Determine the inlet pressure (p1) and the mass flow rate (m.). Round the final answer to three decimal places. The inlet pressure is ----------- lbf/ft2. The mass...
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...
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 through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 321 Inlet pressure: P1 (kPa) = 588 Inlet Velocity: V1 (m/s) = 97 Area at nozzle inlet: A1 (cm^2) =...