An isentropic converging-diverging nozzle receives air from a huge reservoir where the temperature and pressure are 300 K and 400 kPa respectively. The nozzle is designed with throat and exit diameters being 0.2 m and 0.4 m respectively. The nozzle is connected with a 6 m-length adiabatic constant area duct as shown in the figure. If there is a shock wave at the exit of the nozzle, determine: 1. the ratio of duct area at shock wave to critical area for isentropic nozzle (A/A;") 2. Mach number upstream the shock wave (M2) 3. Mach number downstream the shock wave (M). 4. Mach number at the exit of the duct (M2). 5. the pressure at the exit of the duct (Pe). 6. the temperature at the exit of the duct (T2). Take f= 0.002.

An isentropic converging-diverging nozzle receives air from a huge reservoir where the temperature and pressure are 300 K and 400 kPa respectively. The nozzle is designed with throat and exit diameters being 0.2 m and 0.4 m respectively. The nozzle is connected with a 6 m-length adiabatic constant area duct as shown in the figure. If there is a shock wave at the exit of the nozzle, determine: 1. the ratio of duct area at shock wave to critical area for isentropic nozzle (A/A;") 2. Mach number upstream the shock wave (M2) 3. Mach number downstream the shock wave (M). 4. Mach number at the exit of the duct (M2). 5. the pressure at the exit of the duct (Pe). 6. the temperature at the exit of the duct (T2). Take f= 0.002.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Air enters a 5-cm-diameter, 4-m-long adiabatic duct with inlet conditions of Ma1 = 2.8, T1 = 380 K, and P1 = 80 kPa. It is observed that a normal shock occurs at a location 3 m from the inlet. Taking the average friction factor to be 0.007, determine the velocity, temperature, and pressure at the duct exit.
What is the effect of friction on the entropy of the fluid during Fanno flow?
An ideal gas passes a diffuser. At the diffuser inlet, the temperature is T1 = 350.00 K, the pressure P1 = 100.00 kPa, the velocity V1 = 200.00 m/s, and the inlet area A1 = 0.30 m2. At the exit, the velocity is very small. The specific heat of the ideal gas at the constant pressure is cp = 1.0050 kJ/(kg·K). The gas constant is R = 0.2870 kPa·m3/(kg·K). Determine the mass flow rate __________(kg/s)
A large tank supplies helium through a converging-diverging nozzle to the atmosphere. Pressure in the tank remains constant at 8.00 MPa (abs) and temperature remains constant at 1000 K. There are no shock waves in the nozzle. The nozzle is designed to discharge at an exit Mach number of 3.5. The exit area of the nozzle is 100 mm². Determine the mass flow rate through the device. For helium: specific heat ratio k = 1.66; ideal gas constant R = 2077 J/kg.K. To = 1000 K Po= 8 MPa (abs) Throat Helium A₁ = 100 mm² Ma₁ = 3.5
Q1: Air at 35 °C enters a 7-m-long section of a rectangular duct of cross section 15 cm x 20 cm made of commercial steel (&= 0.000045 m) at an average velocity of 7 m/s. Disregarding the entrance effects, determine the fan power needed to overcome the pressure losses in this section of the duct. Air properties at 35 °C: p= 1.145 kg/m³, u = 1.895 x 105 kg/m.s, and v= 1.655 × 105 m²/s.
Air exits from a reservoir maintained at 15 °C and 400 kPa absolute into a receiver maintained at (a) 200 kPa absolute and (b) 100 kPa absolute. If the exit area is 0.001 m², by using equations determine the mass flow rate.
Air flows isentropically from a large reservoir maintained at 597°C and 1.0 MPa absolute into a converging-diverging duct. The flow at the exit plane of diverging duct is supersonic. The duct is 2 m long and has a circular cross sectional area with radius, r in m that varies in axial distance, x along the duct that is defined by r = 0.03x² +0.02 where x extends from -1.0 m to 1.0 m. (a) Sketch a 2D diagram of the above system on a graph of duct radius against axial distance with appropriate labelling. (b) Using the isentropic table provided, determine (i) the Mach number, pressure and temperature at the exit plane, and (ii) the mass flow rate through the duct. E.Q2 (c) If the radius of the duct as specified in E.Q2 is doubled, would the Mach number on the exit plane be increased, decreased or remain unchanged? Explain your answer briefly. Take heat specific ratio of 1.4 and specific gas constant of 0.287 kJ/(kg-K) for air.
Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure and 100°C temperature. State the necessary assumptions and calculate, (a) stagnation temperature (b) stagnation pressure, and (c) stagnation density.(d) With the specified inlet velocity a gas is flowing isentropically in the converging duct. At thethroat if we assume that the velocity is supersonic, how does the mass flow rate be affectedcompared to sonic velocity at the throat. How could supersonic velocity can be achieved in thiscase?
A horizontal air jet with a mass flow rate of (m) and a velocity of (V) strikes the inside surface of a hollow hemisphere. Assume the magnitude of air velocity remains constant ( Vin=Vout=V). Determine the horizontal anchoring force (F) needed to hold the hemisphere in place for the following conditions: m = 4.71 kg/s and V = 20 m/s F F= 11.8 N F=105.9 N F= 47.2 N F=188.4 N
Q3- Air flows from a reservoir and enters a uniform pipe with a diameter of 0.05 m and length of 10 m. The air exits to the atmosphere. The following conditions prevail at the exit: P2 = 1bar, temperature T2 = 27°C and M2 = 0.9. Assume that the average friction factor to be f = 0.004 and that the flow from the reservoir up to the pipe inlet is essentially isentropic Estimate the total temperature and total pressure in the reservoir under the Fanno flow model. %3D M2 0.9 D-0.05 m] L=10 m Po=? To=C T2-27°C P2=1|Bar]
An ideal gas passes a diffuser. At the diffuser inlet, the temperature is T1 = 350.00 K, the pressure P1 = 100.00 kPa, the velocity V1 = 200.00 m/s, and the inlet area A1 = 0.30 m2. At the exit, the velocity is very small. The specific heat of the ideal gas at the constant pressure is cp = 1.0050 kJ/(kg·K). The gas constant is R = 0.2870 kPa·m3/(kg·K). Determine the enthalpy per unit mass at the exit, h2__________(kJ/kg)