For subsonic flow at entry in converging-diverging nozzle flow
at the throat remains Sonic.
Therefore option *C* is correct
2. (5 pts.) Assume air is entering a converging-diverging nozzle with subsonic speed. What are the...
Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions at the throat of the converging-diverging nozzle? (circle all correct answers and assume friction is negligible in the nozzle). a. Subsonic flowb. Supersonic flowc. Sonic flow
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...
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnation pressure upstream of the throat is 8.5 atm and the stagnation temperature is 1000 K. (a) Assume the air is expanded isentropically to supersonic speed at the exit. Determine the following properties at the nozzle exit: Me, Pe, Te, Pe, ue, Poe, Toe (b) If the area ratio in the subsonic part of the converging diverging nozzle, A1/A is...
Problem 2 was...
Air exapands in a frictionless adiabatic flow through a
converging-diverging nozzle at a mass flow rate of 2.5 kg/s. Source
stagnation condition are 1.1 Mpa and 115 C. If the nozzle exit
pressure is 141 kPa, and there are no shocks in the nozzle, find
the (a) the exit area Ae; (b) the throat At.
And I got (a) Ae = 1.11 * 10^(-3) m^2 and (b) At = 1.87 *
10^(-3) m^2
3. For the nozzle...
Consider a converging-diverging nozzle with subsonic inlet conditions. Answer with justification. Use the sketch of the pressure diagram wherever appropriate. Gamma = 1.4. R = 286.9 J/kg-K It is given that when the exit pressure is 1MPa, a certain nozzle is operating under choked, subsonic and isentropic conditions. The mass flow rate is found to be 1000 kg/s. What will be the mass flow rate if the exit pressure is 100 kPa? Explain.
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
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...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...