Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.19P
Prove that the total pressure is constant throughout an isentropic flow.
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Dry saturated steam at a pressure of 8 bar enters a convergent divergent nozzle and leaves it at a pressure of 1.5 bar. If the flow is isentropic and if the corresponding expansion index is 1.135, Determine the ratio of crosssectional area at exit and throat for maximum discharge
Need step by step explanation
Q.2. Air flows through a constant-area duct is connected to a reservoir at a
temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown
in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach
number and the mass flow rate for a back pressure of 0 kPa.
q= 250 kJ/kg
P.= 500 kPa
T; = 500°C
p. = 0 kPa
D=0.02m
Chapter 8 Solutions
Fundamentals of Aerodynamics
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Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Repeat Problems 8.11 and 8.12 using (incorrectly)...Ch. 8 - Derive the Rayleigh Pitot tube formula, Equation...Ch. 8 - On March 16, 1990, an Air Force SR-71 set a new...Ch. 8 - In the test section of a supersonic wind tunnel, a...Ch. 8 - When the Apollo command module returned to earth...Ch. 8 - The stagnation temperature on the Apollo vehicle...Ch. 8 - Prove that the total pressure is constant...
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- Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q = 250 kJ/kg P. = 500 kPa T, = 500°C Po = 0 kPa D = 0.02marrow_forwardAnswer if you are sure about the answer otherwise i will reportarrow_forwardAt a particular operating condition, an axial flow compressor has a reaction of 0.6, a flow coefficient of 0.5 and a stage loading, defined as Aho U2 of 0.35. If the flow exit angles for each blade row may be assumed to remain unchanged when the mass flow is throttled, determine the reaction of the stage and the stage loading when the air flow is reduced by 10% at constant blade speed.arrow_forward
- Dry-saturated steam at 11 bar is passed through a convergent-divergent nozzle and exit pressure is 2 bar. If the flow is isentropic, find exit velocity of the steam and ratio of cross-section at exit to throat. Take index of isentropic expansion of steam = 1.135.arrow_forwardQ.4. Air is fed from a large reservoir, where the temperature and pressure are 280 K and 300 kPa respectively, through isentropic converging-diverging nozzle. The diameters of throat and exit are 0.1 m and 0.15 m respectively. If there is a shock at the exit of the nozzle, determine: 1. the pressure and temperature at the exit of the duct. 2. the mass flow rate. Assume f=0.002arrow_forwardQ.4. Air is fed from a large reservoir, where the temperature and pressure are 280 K and 300 kPa respectively, through isentropic converging-diverging nozzle. The diameters of throat and exit are 0.1 m and 0.15 m respectively. If there is a shock at the exit of the nozzle, determine: 1. the pressure and temperature at the exit of the duct. 2. the mass flow rate. Assume f=0.002 Isentropic Nozzle Adiabatic Duct P, = 300KPA T, = 280 K Normal Shock Wave 5 marrow_forward
- How do I find reservoir pressure given the exit-to-throat area ratio of a supersonic nozzle and a Pitot tube measurement from the test section.arrow_forwardAir enters a turbine at a pressure of 2.2 MPa and a temperature of 816 K. The air exits at a pressure of 50 kPa. Use the following properties for air: R=287 J/kg*K, Cv=718 J/kg*K, Cp=1005 J/kg*K, Y = 1.4 (Use 0 Celsius=273 Kelvin) a. What is the outflow temperature if the turbine is isentropic? b. What is the outflow temperature if the actual turbine has an isentropic efficiency of 94%? c. What is the power output from the actual turbine if the mass flow rate is 8 kg/s?arrow_forwardQ.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q = 250 kJ/kg Pr = 500 kPa Tr = 500°C Po = 0 kPa D= 0.02marrow_forward
- EX: Air at 1 MPa and 600°C enters a converging nozzle with a velocity of 150 m/s. Determine the mass flow rate through the nozzle for a nozzle throat area of 50 cm2 when the back pressure is (a) 0.7 Mpa and (b) 0.4 MPaarrow_forwardAir enters a turbine at temperature and pressure of 800°C, 10bar respectively. The actual exit airtemperature is 180°C. The turbine isentropic efficiency is estimated to be 85%. Calculate the turbine exit pressure and the actual expansion index (n).arrow_forwardAir flows through a converging-diverging (c-d) nozzle. It is supplied from a large air reservoir in which the temperature is 377 K and the pressure is 190 kPa. The velocity and the cross-sectional area at the nozzle exit are 462 m/s and 0.0005 m^2, respectively. Find the followings: Mach number at exit is Area of the throat is The mass flow rate of air is The exit temperature is The exit pressure isarrow_forward
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