AA 283: Aircraft and Rocket Propulsion
Homework 1 Solutions
2014-2015
F. Mechentel, W. Spurlock
Problem 1.1 (10 points)
We are considering the following cross-section :
Note that in this problem, pressures and temperatures are stagnation values. We have t

AA 283: Aircraft and Rocket Propulsion
Homework 5 Solutions
2014-2015
W. Spurlock, F. Mechentel
credits to J. Zimmerman & A. Li
Gas Turbine Power Generator Problem (X points)
We are analyzing a gas-turbine power generator with a recuperator, a heat exchan

AA 283: Aircraft and Rocket Propulsion
Homework 3 Solutions
2014-2015
F. Mechentel, W. Spurlock
Problem 3.7 (35 points)
In this problem we have :
hf = 4.28 107 J/kg
Pt0 = 100
P0
A3
A1.5 = 8
Tt0 = 805.2 K
adiabatic ow, neglect wall friction
= 1.4
Tt

AA 283: Aircraft and Rocket Propulsion
Homework 4 Solutions
2014-2015
F. Mechentel, W. Spurlock
credits to J. Zimmerman & A. Li
Problem 4.5 (15 points)
This problem starts as a simple turbojet, but then we vary Tt4 . The situation is shown below.
First we

AA 283: Aircraft and Rocket Propulsion
Homework 2 Solutions
2014-2015
F. Mechentel, W. Spurlock
Problem 2.1 (8 points)
In this problem we examine the eect of heat loss due to conduction in a ramjet combustor. The energy balance
in (2.19) was derived by ap

CHAPTER 8
MULTISTAGE ROCKETS
With current technology and fuels and without greatly increasing the effective I sp by airbreathing, a single stage rocket to orbit is still not possible. So it is still necessary to reach
orbit using a multistage system where

CHAPTER 4
THE TURBOJET CYCLE
4.1
THERMAL EFFICIENCY OF THE IDEAL TURBOJET
Recalling our discussion in Chapter 2, the thermal efciency of a jet engine propulsion system
is dened as
" kinetic energy of air " kinetic energy of fuel
Power to the vehicle + - +

CHAPTER 7
ROCKET PERFORMANCE
7.1 THRUST
The gure below shows a sketch of a rocket in a test stand. The rocket produces thrust, T , by
expelling propellant mass from a thrust chamber with a nozzle. The test stand applies an oppo
site force on the rocket ho

CHAPTER 1
PROPULSION SYSTEM THERMODYNAMICS
1.1 INTRODUCTION
The gure below shows a cross-section of a Pratt and Whitney JT9D-7 high bypass ratio turbofan engine. The engine is depicted without any inlet nacelle or nozzle.
ma
ma
ma
fan
fan
station 3
940F
3

Gas turbine based power generation
Siemens SGT6-5000F(4) 150 MW power Gas Turbine
h fCH 4 = 5.543 10 7 J / kg
Cycle Analysis
Across the burner.
5.543 10 7
f =
=
= 185
C pT0 1005 298.15
hf
Power balance.
Divide by
maC pT0
Work output coefficient.
The syste

CHAPTER 10
SOLID PROPELLANT ROCKETS
10.1 INTRODUCTION
The sketch below shows a section view of a typical solid propellant rocket.
motor case
nozzle
propellant grain
port
igniter
propellant grain
1
2
A
*
Figure 10.1 Solid rocket cross section
There are bas

AA283
Aircraft and Rocket Propulsion
Chapter 8 - Multistage Rockets
7.1
Notation
7.2
Analysis
(8.2)
(8.3)
(8.4)
(8.5)
(8.6)
(8.7)
8.3
The variational problem
8.4
Example - Exhaust velocity and
structural coefficient the same for all stages.
There is very

CHAPTER 9
THERMODYNAMICS OF REACTING MIXTURES
9.1 INTRODUCTION
For an open system containing several reacting chemical species that can exchange mass
and work with its surroundings the fundamental Gibbs equation relating equilibrium
states is
I
K
i=1
k =1

CHAPTER 6
THE TURBOPROP CYCLE
6.1
PROPELLER EFFICIENCY
The turboprop cycle can be regarded as a very high bypass limit of a turbofan. Recall that the
propulsive efciency of a thruster with P e = P 0 and f 1 is
2
! pr = - .
1 + Ue U0
(6.1)
This expression

CHAPTER 11
HYBRID ROCKETS
11.1 HYBRID ROCKETS VERSUS CONVENTIONAL SYSTEMS
Liquid bi-propellant systems
A liquid bi-propellant chemical rocket system is shown schematically below. Oxidizer and fuel
from separate tanks are pressure-fed or pump fed into a co

AA283
Aircraft and Rocket Propulsion
Chapter 11 - Hybrid Rockets
All modern launch systems use conventional
solid and/or liquid rocket propulsion systems
Liquid Main Engines
High performance
and throttle-able
but
complex, expensive,
explosion hazard.
Worl

CHAPTER 3
THE RAMJET CYCLE, SCRAMJETS
3.1
RAMJET FLOW FIELD
Before we begin to analyze the ramjet cycle we will consider an example that can help us understand how the ow through a ramjet comes about. The key to understanding the ow eld is the
intelligent

CHAPTER 2
ENGINE PERFORMANCE PARAMETERS
2.1
THE DEFINITION OF THRUST
One might be surprised to learn that there is no direct way to determine the thrust generated by
a propulsion system. The reason for this is that the ow over and through an installed eng

AA283 Homework 4 2016 -2017
Due Tuesday February 7
Reading: remainder of Chapter 4
Problems:
Chapter 4 - Problems 9, 10, 14, 17 and 19
From the 2015 midterm
Problem In Chapter 2 we studied two of the three classical thermodynamic cycles, the Carnot cycle

AA283 Homework 5, 2016 -2017
Due Tuesday February 14
Reading: Notes on gas turbine power generation on my website, Chapter 5
Problems:
Problem - In class we discussed the example of a power gas turbine equipped with a recuperator. In that
example we assum

AA283 Homework 8 2016 -2017
Due Thursday March 9
Reading: Chapter 9
Problems:
Chapter 9 - Problems 1, 2, 3.
Compare your results to the predictions of the performance of metallic hydrogen described by Silvera and
Cole. You can find the paper at
https:/das

AA283 Homework 7 2016 -2017
Due Tuesday February 28
Reading: Chapter 8
Problems:
Chapter 7 - Problems 5 and 6
Chapter 8 Problems 1 and 2
From a previous final exam
Problem The figure below depicts a monopropellant thruster based on release of an ideal gas

AA283 Homework 6 2016 -2017
Due Tuesday February 21
Reading: Chapters 6 and 7
Problems:
Chapter 6 Problems 1 and 7
Chapter 7 - Problems 1, 3 and 4
From last years final exam
Problem A large UAV in hover, U 0 = 0 , uses four turboprop engines for propulsio

B. Cantwell, Jan 2017
STANFORD UNIVERSITY Department of Aeronautics and Astronautics
AA 283 Aircraft and Rocket Propulsion Winter 2016-2017
Instructor: Brian Cantwell, 379 Durand, x 3-4825, [email protected]
Class hours: TTh 10:30-11:50
Instructor off

AA 283: Aircraft and Rocket Propulsion
Homework 6 Solutions
2014-2015
F. Mechentel, W. Spurlock
Problem 6.2 (5 pts)
We need to show that the velocity of the propeller is approximately
U2 = U13 =
U0 + U6
2
Using the equation of momentum :
F = mU6 mU0 = m(U

AA 283: Aircraft and Rocket Propulsion
Homework 7 Solutions
2014-2015
F. Mechentel, W. Spurlock
credits to J. Zimmerman & A. Li
Problem 7.1 (12 pts)
Our setup for this problem is shown below, with a pretty picture stolen from wikipedia.
We need to nd the

AA 283: Aircraft and Rocket Propulsion
Homework 9 Solutions
2014-2015
F. Mechentel, W. Spurlock
credits to J. Zimmerman & A. Li
Problem 10.1
If it's a beautiful summer day, we can consider that the ambient temperature is higher than usual. In this case,
t