Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.14P
Derive the Rayleigh Pitot tube formula, Equation
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Consider a regenerative gas turbine power plant with two stages of compression and two stages of expansion.
The compressor pressure ratio of the compressor is 3. Air enters each stage of compressor at 290 K and each
stage of turbine at 1400 K. The regenerator has an effectiveness of 100%. Determine
(a) The enthalpy at stage#2 in KJ/kg⭑
(b) The enthalpy at stage#6 in KJ/kg*
(c) The enthalpy at stage#9 in KJ/kg
(d) The enthalpy at stage#10 in KJ/kg
(e)The mass flow rate of air needed to develop a net power output of 50 MW*
*For all final answers please enter the integer part only, (ie 1234) and do not include the decimal part
and the decimal point
No rounding in your calculation.
Compressor
stage 1
Regenerator
www
HX
ww
9
Combustor
Reheat
Intercooler
ww
Compressor
stage 2
Turbine 1
combustor
Turbine 2
Design a proportional derivitivecontroller for a plant orsystemthat satisfies the following specifications :
1. is steady-state error is less than 2 % for a ramp input.
2.) Damping ratio (zeta) is greater than 0.7have determined the
3. Once youvalue of kp and kd, then plotthe response of the compensated(with controller) and uncompensated( without the controller, only the plantsystem using MATLAB.
Example 2
The particle has a mass of 0.5 kg and is confined to move
along the smooth horizontal slot due to the rotation of the
arm OA. Determine the force of the rod on the particle and
the normal force of the slot on the particle when 0 = 30°.
The rod is rotating with a constant angular velocity
2 rad/s. Assume the particle contacts only one side of
the slot at any instant.
B
=2 rad/s
0.5 m
0.5(9.81)N
r
F
30°
N
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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