Consider a Mach 3 flow at 1 atm pressure initially moving over a flat horizontal surface. The flow then encounters a 20 degree expansion corner, followed by a 20 degree compression corner that turns the flow back to the horizontal. Calculate the pressure of the flow downstream of the compression corner. Note: You will find that the pressure downstream of the compression corner is different from the pressure upstream of the expansion corner, even though the upstream and downstream flows are in the same direction, namely horizontal. Why?
Trending nowThis is a popular solution!
Chapter 9 Solutions
Fundamentals of Aerodynamics
Additional Engineering Textbook Solutions
DESIGN OF MACHINERY
Vector Mechanics For Engineers
Foundations of Materials Science and Engineering
EBK FUNDAMENTALS OF THERMODYNAMICS, ENH
Heating Ventilating and Air Conditioning: Analysis and Design
Vector Mechanics for Engineers: Statics
- Find the velocity of bullet fired in standard air if the Mach angle is 45°. Take R=287.14 J/kg K and k = 1.4 for air. Assume temperature as 27°Carrow_forwardCalculate the Stagnation temperature for steam flowing at 0.1MPa, 350 degC and 480 m/s. Calculate the stagnation pressurearrow_forwardFor non-isentropic constant-area flow with stagnation temperature change the following relation was determined: Y 1 To _ ²(y + 1)M² (1 + ¹ Z ¹ M²) 2 TO (1+yM²)² It is possible to use the above equation and calculate the downstream Mach number without resorting to iteration for a flow where the upstream Mach number, as well as the upstream and downstream stagnation temperatures, are known. This is a common calculation for flows through engine combustors. Presuming the left side is a known quantity, show that the above equation can be directly solved as a quadratic in M² and which roots correspond to the subsonic/supersonic solution. Rewrite the equation as: aM4 + bM² + c = 0, and then M² = (−b ± √b² - 4ac)/2a. Determine the appropriate expressions for a, b, and c.arrow_forward
- Find the expression for the ratio of the stagnation pressure after a shock wave to the static pressure before the shock wave as a function of k and the Mach number upstream of the shock wave Ma1arrow_forwardConsider a compressible airflow through a pipe. If the flow velocity all throughout the tube is always below Mach 1, what happens to the flow velocity if the cross-sectional area of the pipe at the exit is increased?arrow_forwardThe tank is filled with air at 20°C and 139 kPa in stationary condition. Air is leaving the tank with flowing in a nozzle under steady-state condition. The flow is under isentropic and subsonic condition. The nozzle exit area is 18,59 cm?. After leaving from the nozzle, air strikes a vertical plate. Define the force [N] required to hold the plate stationary. (Note: Assume Pe=1 atm, kair=1.4, Rair=287 J/kg.K) Pte F Yanıt:arrow_forward
- Example: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and 200°C with a low velocity. It expands after the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to a pressure drop of 200 kPaarrow_forwardConsider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction. Calculate the amount of heat per unit mass (in joules per kilogram) necessary to choke the flow at the exit of the duct for an inlet Mach number of M1 = 2.2.arrow_forwardAir at 50 Kpa, 300 K, and Mach 2.0 passes through a normal shock. Determine: a) Total temperature and pressure upstream of the shock b) Total temperature and pressure downstream of the shock. I bakarrow_forward
- Q.2 Air which enters a diverging duct is slowed by a normal shock wave, as shown in figure. The airstream enters the duct at a Mach number of 3 and leaves it at a Mach number of 0.4. the exit cross-sectional area of the duct is twice the inlet cross- sectional area. Determine the pressure ratio across the normal shock wave, and the ratio of the exit pressure to the inlet pressure. M. = 0.4 M; = 3arrow_forwardAir at 27 °C and 100 kPa enters in a steady flow to a nozzle at a velocity of 100 m/s. If the inlet area of the nozzle is 0.5 m², what is the mass flow rate through the system?arrow_forwardAir at 25 psia, 320°F, and Mach number Ma = 0.7 flows through a duct. Calculate the velocity and the stag nation pressure, temperature, and density of air.arrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY