5 Consider the subsonic flow through a divergent duct with area ratio A2/A, 1.7. If the inlet conditions are T, = 300 K and uj = 250 m/s, and the pressure at the exit is p2 = 1 atm, calculate: a. Inlet pressure pj b. Exit velocity uz. %3D

Q: A convergent-divergent nozzle with throat area of 35cm². At a point downstream of the throat area,…

A: Nozzle type= Convergent-Divergent nozzle Area of throat Ao= 35 cm2 V1 = 155 m/s T1 = 330K P1 =…

Q: Air discharge through a nozzle. A normal shock wave occurs at section of the flow at which the Mach…

A: Given Data At the inlet Ma1=2.5 P1=40KPa T1=-20C=253K For air Y=1.4

Q: What would you have to do to reduce this flow angle to zero degrees?

A: Here the reducing flow by zero degree angle attack

Q: A normoa shock wave exists in air flow with up stream M=2 and a pressure of 20kpa and temperature of…

A: Given: Upstressm properties: Mx=2Px=20kPaTx=15°C or 288K Solution: Downstream mach number is given…

Q: JI Air stream flow in a convergent - divergent nozzle, with a stagnation pressure of 120 kPa, the…

A:

Q: A commercial aircraft flies at 0.86 at altitude of 10000 feet above sea level. The inlet has been…

A: Given:  gamma = 1.38 Mach number , M = 0.86 pressure recovery = 0.96

Q: The velocity of flow after a normal shock wave when (Tx= 315 K, vx= 555 ms-1)

A:

Q: In a convergent nozzle the flow conditions are subsonic. As the flow progresses the velocity of…

A:

Q: An unconfined supersonic flow passes over the contoured wall shown below. The wall segment AB is a…

A: Given:To Find:Wall static pressures at B and C.

Q: Q3. A supersonic flow of air has a pressure of 1 x 105 N/m2 and My a temperature of 350 K. After…

A: given data;⇒pressure(P)=1*105N/m2⇒temperature(T)=350K⇒mack number(M)=3.5

Q: Q.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is…

A: Please find the solution below

Q: In a divergent nozzle the flow conditions are subsonic. As the flow progresses the velocity of flow:…

A:

Q: The velocity of flow after a normal shock wave when (Tx= 315 K, vx= 555 ,ms-1) 275.7 ms-1 O 282.6…

A: Given: Temperature (T) = 315 K Velocity (Vx) = 555 m/s To find: Velocity after shock

Q: 54. Engine for an airplane (Fth = 30.6 kN, A, = 2.8 A2, p1 = 101.3 kPa, T1 = 12 °C, v1 = 105.4 m-s1,…

A: By using the momentum integral equation P1A1-P2A2-Fth=m˙v2-v1    ....(1) Now the mass flow rate is…

Q: e end of the pipe. If the number, the mass flow

A:

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: Air flows subsonic in the duct, ignoring friction and heat of 984 kJ/kg. Pressure drop from p,= 220…

A: GIven DataP1=220kPaP2=116kPaT01=305Kq=984kJ/kg

Q: O. sir with an initial speed of vo 10 m/s (Fig. 7.28). Assume that %3D %3D e the ball to ascend and…

A:

Q: equal to 3.0. Find Me, Pe, and the loss in stagnation pressure (Poi - Poe). Repeat for a ock at the…

A: Given Image,

Q: Supersonic air takes a 5° compression turn, as inFig. . Compute the downstream pressure and…

A: Write the given information.

Q: b) Air at 300 K and 100 KPa passes between two parallel plates which are 30 mm apart. The flow is…

A:

Q: Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A1 = 2 m2…

A: Given:A1=2 m2A2=0.5 m2P2=1 atm =101.325 KPaV2=40 m/s

Q: 45. 4.7. The temperature of argon is 100 F, the pressure 42 psia, and the velocity 2264 ft/ sec.…

A:

Q: IT or F 1/The Mach number and speed of the flow also decrease across a shock wave. 2/the total…

A: “Since you have posted a multiple question, we will provide the solution only to the first three…

Q: Q2/ Air flows isentropically in a converging-diverging nozzle with initial Ma = 0.2, pressure = 1…

A:

Q: he entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1)

A: Given data: Tox = 505 K Vx = 490 m/s For air, specific heat, cp = 1.005 kJ/kg.K = 1005 /kg.K Gas…

Q: Air enters a pipe of 1in diameter at subsonic velocity and P: 30 psia, T-550 "R. If the pipe is 10ft…

A: Given: d=1 inP1=30 psiaT1=550 RL=10 ftf=0.025P2=20 psiaγair=1.4 To find: Mass flow Mach number at…

Q: Determine the location of a stationary normal shockwave in a C-D nozzle. The back-pressure to…

A: Step 1: Understanding the problemThe problem asks us to determine the location of a stationary…

Q: Q1// Air stream flow in a convergent- divergent nozzle, with a stagnation pressure of 120 kPa, the…

A: The nozzle is both convergent and divergent. The forward section of the nozzle is convergent,…

Q: Reservoir Temperature in degrees Rankine

A: I have answered this question in step 2.

Q: the flow via a chemical reaction taking place inside the duct. Determine the heat transfer rate…

A:

Q: Q3: Supersonic divergent duct with Mach inlet 3 and exit Mach number equal to 0.4. Normal shock wave…

A: Given, Inlet Mach number, M1=3AiAi*=4.2346Outlet Mach number,M2=0.4AeAe*=1.5901AlsoAiAe=0.5 (Given…

Q: convergent nozzle of exit area 0.05 m2 is used to exhaust this gas to an ambient pressure of 100 kPa…

A:

Q: e Tr1 = 650°R and q* = 500 BTU/lbm, respectively. Calculate a) the inlet Mach number Mị b) exit…

A:

Q: (Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the…

A:

Q: b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the…

A: Note:  5.198 is given in question by mistake. It must be 0.5198 for upstream mach.