Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air through a convergent-divergent nozzle. The stagnation temperature = 300K, stagnation pressure at the inlet = 107500Pa, static pressure at the exit=4400Pa, C1 is a constant = 0.1097 for calculating circular cross-sectional area of a convergent-divergent nozzle: A = C1 + x^2 and x (axial distance from the throat) =1m. γ = 1.4 and R=287. Calculate the mass flow rate of air through the nozzle.

Q: Engineers call the supersonic combustion in a scramjetengine almost miraculous, “like lighting a…

A: Given Data: The area at section 1 and 4 is: A1=1 m2. The area at section 2 and 4 is: A2=0.2 m2. The…

Q: Q2: Air (y = 1.4) enters a converging-diverging diffuser with a Mach number of 2.8, static pressure…

A:

Q: Air at 800 kPa and 1200 K enters a converging nozzle with negligible velocity (i.e., these are…

A:

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: Compute stagnation enthalpy of air at normal conditions (P=1atm, T=300K) moving with velocity of…

A: Write the equation for the stagnation enthalpy. h0=h+v22   =CpT+v22 Here, The stagnation enthalpy is…

Q: Please answer c A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its…

A:

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

A:

Q: Please show all work of a,b,&c. A supersonic converging-diverging nozzle is near the exit of a…

A: A2/A1 = (1/M2) * [(2/(γ+1)) * (1 + (γ-1)/2 * M2^2)]^((γ+1)/(2*(γ-1))) A2/A1 = (1/M2) * [(2/(γ+1)) *…

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

A:

Q: Design the 2D steady MOC contour for a super sonic nozzle assuming that the expansion section is a…

A: To design the 2D steady Method of Characteristics (MOC) contour for a supersonic nozzle, we need to…

Q: Q3. A supersonic flow of air has a pressure of 1 x 10 N/m² and a temperature of 350 K. After…

A: A supersonic flow of air expands through 35° turn Mach number M1=3.5θ=35°flow deflectionM2=?

Q: 3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is…

A: a. V=2832.61sm​,T0​=4219.872K,P0​=32962kPab. vs​=1303.87m/s, T0s​=77941K, P0s​=3392510kPac.…

Q: Consider a normal shock wave in air. The upstream conditions are given by M , = 3, p, = 1 atm. and…

A:

Q: Air at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the…

A: Dear Students

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: Air flows in the channel in the figure below. The pressure at station 1 is 59 psia. Determine the…

A: Given data:

Q: a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation…

A:

Q: 1) What is the value of static temperature, stagnation temperature and stagnation pressure in the…

A: To calculatethe static temperature, stagnation temperature and stagnation pressure in the test…

Q: At a certain point in a pipe, air flows steadily with a velocity of 150 m/s and has a static…

A: DISCLAIMER FOR MULTIPLE Since you have asked multiple questions, we will solve the first question…

Q: Air enters a converging/diverging nozzle (diameters : 4mm , 2 mm 8 mm) at 1400 kpa and 200 C. the…

A: Convergent divergent nozzle In this type of nozzle at the inlet the nozzle is convergent that is it…