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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Chapter 8 Solutions
Fundamentals of Aerodynamics
Ch. 8 - Consider air at a temperature of 230 K. Calculate...Ch. 8 - The temperature in the reservoir of a supersonic...Ch. 8 - At a given point in a flow, T=300K,p=1.2atm, and...Ch. 8 - At a given point in a flow, T=700R,p=1.6atm, and...Ch. 8 - Consider the isentropic flow through a supersonic...Ch. 8 - Consider the isentropic flow over an airfoil. The...Ch. 8 - The flow just upstream of a normal shock wave is...Ch. 8 - The pressure upstream of a normal shock wave is 1...Ch. 8 - The entropy increase across a normal shock wave is...Ch. 8 - The how just upstream of a normal shock wave is...
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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- Air enters a converging–diverging nozzle at a pressure of 1200 kPa with negligible velocity. What is the lowest pressure that can be obtained at the throat of the nozzle?arrow_forwardDiscuss the different types of aircraft gas turbine engines and their applications.arrow_forward-The throat area of a c-d nozzle is 10 cm^2 and its exit is 20 cm^2. If the stagnation pressure is 1 bar, what is the exit pressure (Pe) range needed to chock the throat? choese 1-greater or equal 0.0935 bar and less or equal 0.937 bar 2-less or equal 0.937 bar 3- greater or equal 0.937 bar and less or equal 1 bar 4- greater or equal 0.935 bararrow_forward
- If a calorically perfect gas flow is steady, isentropic and one dimensional, which of the following quantities do not change? Total enthalpy, total temperature, statics temperature, total pressure, static pressure, total density, static density, critical temperature, critical pressure, critical density, characteristic Mach number, entropy, enthalpy.arrow_forwardEach stage of an axial flow compressor is of 0.5 reaction, has the same mean blade speed and the same flow outlet angle of 30 degree relative to the blades. The mean flow coefficient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m. Using compressible flow analysis determine the axial velocity and the mass flow rate.arrow_forwardWhat is the pressure ratio of the High-Pressure turbine operating at cruise? Given data: Mach number = 0.8 Altitude = 40000 ft High pressure Compressor ratio = 18 booster pressure ratio = 1.66 Fan Pressure Ratio = 1.5 Cp = 1244J/kgK polytropic efficiency =0.9 ? = 1.3arrow_forward
- Show all work neatlyAir flows through an Isentropic Nozzle with an inlet temperature of 660 degrees R, an inlet velocity of 40 Ft/Sec, and an inlet Pressure of 140 PSIA. The Air exits with an exit Pressure of 15 PSIA.Determine the Following: ) Exit Temperature_______________Degrees Rankine ) Exit Velocity___________________Ft / Secarrow_forwardA small ramjet engine is to be designed for a maximum thrust of 1000 lb at sea level at a velocity of 950 ft/s. If the exit velocity and pressure are 2000 ft/s and 1.0 atm, respectively, how large should the inlet be?arrow_forwardNon-isentropic flow regime in the converging-diverging nozzle is restricted between chocking and exit shock conditions 1-True or 2-flase ??arrow_forward
- What are opposed piston, X-type, and H-type engines? Explain each of them with applications.arrow_forward12- Combustion gases (k=1.33) enter a convergent nozzle at a stagnation temperature of 350 oC and a stagnation pressure of 430 kPa and are vented to the atmosphere at 20 oC, 100 kPa. Which of the following is the lowest pressure that will occur in the nozzle?arrow_forwardA convergent-divergent nozzle with an exit-to-throat area ratio of 1.616has exit and reservoir pressures equal to 0.947 and 1.0 atm, respectively.Assuming isentropic flow through the nozzle,calculate the mass flow through the nozzle, assuming that the reservoir temperature is 288 K and the throat area is 0.3 m2.arrow_forward
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