Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
6th Edition
ISBN: 9781259683268
Author: Anderson, John
Publisher: Mcgraw-hill Higher Education (us)
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Chapter 10, Problem 10.8P
For the flow in Problem 10.7, calculate the mass flow through the nozzle, assuming that the reservoir temperature is 288 K and the throat area is
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Chapter 10 Solutions
Connect with LearnSmart for Anderson: Fundamentals of Aerodynamics, 6e
Ch. 10 - The reservoir pressure and temperature for a...Ch. 10 - A flow is isentropically expanded to supersonic...Ch. 10 - A Pitot tube inserted at the exit of a supersonic...Ch. 10 - For the nozzle flow given in Problem 10.1, the...Ch. 10 - A closed-form expression for the mass flow through...Ch. 10 - Prob. 10.6PCh. 10 - A convergent-divergent nozzle with an...Ch. 10 - For the flow in Problem 10.7, calculate the mass...Ch. 10 - Consider a convergent-divergent nozzle with an...Ch. 10 - A 20 half-angle wedge is mounted at 0 angle of...
Ch. 10 - The nozzle of a supersonic wind tunnel has an...Ch. 10 - We wish to design a supersonic wind tunnel that...Ch. 10 - Consider a rocket engine burning hydrogen and...Ch. 10 - For supersonic and hypersonic wind tunnels, a...Ch. 10 - Return to Problem 9.18. where the average Mach...Ch. 10 - Return to Problem 9.19, where the average Mach...Ch. 10 - A horizontal flow initially at Mach I flows over a...Ch. 10 - Consider a centered expansion wave where M1=1.0...
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- Please attached photo. I have theoretically solved this using only equations I can’t find a way to solve without the mass flow rate or area of the inlet as a given.arrow_forwardA double-tank system in Fig. has two identical convergingnozzles of 1-in2 throat area. Tank 1 is very large,and tank 2 is small enough to be in steady-flow equilibriumwith the jet from tank 1. Nozzle flow is isentropic,but entropy changes between 1 and 3 due to jet dissipationin tank 2. Compute the mass flow.arrow_forwardQ5: A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is Po and exhausts to the atmosphere with a pressure of Po. The area A at distance x from the throat is given by (A = At (1 + 0.75x/L)), where At is the throat cross- sectional area and Lis the total length of the diverging part of the nozzle. At a certain pressure ratio PoPb, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio P/Po. Ans.: 0.45 L = 0.753 Р. Psarrow_forward
- Q1: A converging-diverging frictionless nozzle is used to accelerate an airstream emanating from a large chamber. The nozzle has an exit area of 30cm² and a throat area of 15cm². If the chamber temperature is 500K, and the back pressure is 101kPa, calculate the following: a. Minimunt chamber pressure (po) to choke the nozzle. b. Mass flow rate for a chamber pressure (po) of 400kPa. c. Mass flow rate for a chamber pressure (po) of 105kPa.arrow_forward1. At what flow angle will the flow become just sonic downstream of the nozzles of a high pressure turbine? The nozzles discharge into an annulus which has a shroud diameter of 250 mm and hub to the shroud diameter ratio is 0.80. The stagnation pressure and temperature are 1500 kPa and 1277 0 C respectively. The mass flow rate is 7 kg/s. The value of R is 286.96 J/(kg.K) and Cp/ R is 4.1arrow_forward6.6. Air flows through a 0.25 m diameter duct. At the inlet the velocity is 300 m/s, and the stagnation temperature is 360 K. If the Mach number at the exit is 0.3, determine the direction and the rate of heat transfer. With the same conditions at the inlet, determine the amount of heat that must be transferred to the system if the flow is sonic at the exit.arrow_forward
- A 4.5 m diameter diesel tank has an outlet nozzle of 75 mm in diameter. What is the mass flow rate in kg/s of through the nozzle if specific gravity of diesel is 0.85? Volume of the tank when full is 150000 L.arrow_forwardAir is flowing in a duct with velocity of 7.62 m/s and static pressure of 2.7 cmWG. The duct diameter is 1.22 m and the barometric pressure is 99.4 kPa and the gage fluid temperature and air temperature is 30 degC. What is the total pressure against which the fan will operate in mm of water? and What is the required motor brake power in Question no. 4 assuming a mechanical efficiency of 89%.arrow_forwardWater enters at section 1 at 10 m/s with sp gr of 0.998 and alcohol enters sections 2 at 6 m/s with sp gr of 0.8. Pipes 1, 2 are of 3 cm in diameter and pipe 3 is of diameter 4 cm. Compute the exit velocity and density of the mixture. Assume ideal mixing of incompressible fluids. Please provide complete solutionarrow_forward
- QUESTION 2 A compressor blade design tested in a cascade is found to choke with an inlet Mach number of 0.9 when the inlet flow angle is 52 deg. If the ratio of the throat area to the frontal area, A*/H1s, for the cascade is).625, calculate the loss of stagnation pressure between the far upstream and the throat and express this as a loss coefficient. Give your comments on what could cause this loss.arrow_forwardA duct 0.40 m high and 0.80 m wide suspended from the ceiling in a corridor, makes a right angle turn in the horizontal plane. The inner radius is 0.2 m and the outer radius is 1.0 m measured from the same center. The velocity of air in the duct is 10 m/s. Compute the pressure drops in this elbow. Assuming friction factor of 0.3, density of 1.204 kg/m3 and length of 10 m. Group of answer choices 441 Pa 143 Pa 341 Pa 413 Pa please provide complete sollution for analysis and reviewarrow_forward3. Assume the turbine as an incompressible flow machine. The average meridional speed is given as 150m/s. The flow coefficient is 0.5. Determine the blade speed that satisfies the above conditions.4. In a two-dimensional compressor cascade, inlet stagnation air pressure is 1.5 bar and inlet stagnation temperature is 330K. For an inlet Mach number of 0.75 and an inlet flow angle of 500, the exit flow angle is measured as 15.80. Determine the mass flow rate per unit frontal area, the exit Mach number and the static pressure ratio across the cascade. Assume the flow is isentropic.arrow_forward
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