Mm=15
_._
p.14
Figlm 1-5.4
Case I: Earn angie qfa'ck.
First draw a gure cfw_exaggerated shunning the ames acting on the mufer
ID"
141'
l"r
1111 = EFT = magma1111111111 =11
F111 1.1, = 2-5, a =5 using Cuars 111111111111an 51111 a = 21.4221. 1111111 11111
Chapter 6 Differential Analysis of Fluid Flow
Inviscid flow: Eulers equations of motion
Flow fields in which the shearing stresses are zero are said
to be inviscid, nonviscous, or frictionless. for fluids in
which there are no shearing stresses the normal
EAS 4134 Project II
Due Tuesday, Dec. 6th at the final exam
Supersonic Wind Tunnel Design
To receive credit, you need to show all your steps, clearly state your assumptions and answer
the questions in a clear, logical manner.
You are asked to do some prel
EAS 4134 Project I
Due Tuesday, November 8th at the beginning of class
Hypersonic Advanced Propulsion Technology:
The Propulsion & Energy Research Laboratory at University of Central Florida is
working on the research development of an advanced propulsion
EAS 4134 Homework 6:
Fano Flow
Due Thursday, November 17th at the beginning of class
Show all your steps and state your assumptions, clearly
1. Find the time required for the pressure in the tank filled with Nitrogen( = 1.4 and R
= 296.8 J/kg K) to drop f
EAS 4134 Homework 3:
Normal Shocks
Due Thursday, October 6th at the beginning of class
A large air storage tank is venting through a nozzle with a throat diameter of 5 cm and
an exit diameter of 6 cm. The tank pressure is fixed at 5 MPa while the ambient
EAS 4134 Homework 4:
Moving Shocks and Oblique Shocks
Due Tuesday, October 18th at the beginning of class
Show all your steps and state your assumptions, clearly
1)
2) A shock wave propagates down a constant area duct into still air at 100 kPa and a
tempe
EAS 4134 Homework 5:
Oblique Shocks and Expansion Fans
Due Thursday, November 10th at the beginning of class Show all your steps and state
your assumptions, clearly
1.
2.
3. Find the Mach numbers on all of the airfoil surfaces and Lift and Drag forces on
EAS 4134 Homework 2:
Fundamental concepts, Isentropic compressible flow fundamentals
Due Tuesday, September 13th at the beginning of class
1) Sonic velocity through Air is 275 m/s. What is the temperature in Kelvin?
2) A pilot measure the ambient pressure
EAS 4134 Homework 1:
Conservation of Mass, Momentum, Energy and Fundamental concepts
Due Tuesday, September 6th at the beginning of class
1) A jet engine produces 500 kN of thrust. The velocity at the exit plane is 600 m/s, and
the diameter of the engine
EAS 4134 Homework 7:
Rayleigh Flow
Due Thursday, December 1st at the beginning of class
Show all your steps and state your assumptions, clearly
1.
2. A constant-area combustion chamber is supplied air at 200K and 70kPa. The air
stream has a velocity of 15
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EAS 4134 Homework 1 Solution:
Conservation of Mass, Momentum, Energy and Fundamental concepts
1) A jet engine produces 500 kN of thrust. The velocity at the exit plane is 600 m/s, and
the diameter of the engine exhaust nozzle is 1 m.
The mass flow rate th
EAS 4134 Homework 2 Solution:
Fundamental concepts, Isentropic compressible flow fundamentals
1) Sonic velocity through Air is 275 m/s. What is the temperature in Kelvin?
2) A pilot measure the ambient pressure of 207 kPa and stagnation pressure of 278 kP