MAE 02 Introduction to Aerospace Engineering
Homework Set #2 Due WED 23 OCT 2013
Name: _
ANSWERS: (Turn in only this sheet)
Problem 2.1
Exit Velocity = _ m/s
Problem 2.2
a. 810 m/s
b. 960 m/s
c. 1240 m/s
d. 3970 m/s
Problem 2.3
a. 1940 m/s
b. 5950 m/s
c.
MAE 2 Homework #4 (Fall 2010) Note: Some numbers and wording may be changed relative to the textbook When differences occur, this assignment sheet has precedence.
problems. Problem A
Find the neutral point and static margin for the DC-8-50 turbofan commer
Turning Flight
Force Balance in Turn
Load Factor
Turn Rate and Radius
Wing Loading
MAE 2
Vertical Force Balance
A level turn implies that the airplane flight path changes, but is still restricted to a
horizontal plane.
By banking the wings, the lift vecto
V-n Diagrams
Corner Speed
Load Limits
V-n Diagram
Load Distribution
NASA Image
MAE 2
Load Factor
Recall that the aircraft load factor is defined as the ratio of lift to weight.
L
n
W
n=load factor
L=lift
W =weight
Load factor will be equal to unity (n = 1
Rocket Equation
Rocket Equation
Burnout Velocity
Staging
Maneuver Propellent
NASA Image
MAE 2
Forces Acting on the Rocket
Neglect drag force (for now).
Assume rocket weight is small when compared to the massive engine thrust.
T D Mg=M
T
Mg0
T =M
dV
dt
dV
Structural Analysis
Stress
Safety Factor
Bending Moment
Wing Spars
MAE 2
Stress
A load (force) applied to a structural element causes stress in the material.
F
F
F
Tension:
Force Balance:
F
F
Compression:
F A=0
=
F
A
=stress
F =applied force
A=cross secti
Aircraft Stability
Longitudinal Stability
Pitch Moment Coefficient
Stability Criteria
Conventional Aircraft
Canard Aircraft
Flying Wings
NASA Image
MAE 2
Longitudinal Stability
Will the aircraft inherently generate a pitching moment that opposes a disturb
Airplane Build Project
Gliding Flight
Payload Electronics
KF Airfoil
Example Analysis
Flight Testing
MAE 2
Airplane Project
Three-person teams will design, build, and fly a self-steering glider.
The design objective is to maximize flight endurance while t
Airfoils
Nomenclature
Aero Coefficients
Airfoil Data
Stall Speed
Flaps
MAE 2
Airfoil Nomenclature
The cross-sectional shape of a wing (or tail surface) is called an airfoil.
Thickness
Leading edge
Mean Camber Line
Camber
Chord Line
Airflow
Trailing Edge
C
Drag Polar
Wake Vorticies
Induced Angle-of-Attack
Induced Drag
Drag Polar
Campbell, J.F., and Chambers, J.R., Patterns in the Sky, NASA SP-514, 1994.
MAE 2
Wake Vorticies
A wake vortex is created by air leaking around the tips of a finite-length wing.
Pre
Gliding Flight
Glide Angle
Force Balance
Wing and Tail Lift
Trim Angle-of-Attack
NASA Image
MAE 2
Free Body Diagram
Forces acting on the airplane include:
Lift (L) acts perpendicular to the flight path direction
Drag (D) acts parallel (but opposite) to fl
A Brief History of Aviation
Lighter-Than-Air
Heavier-Than-Air
Early Construction
San Diego
High Performance
Unmanned
Rotorcraft
Air Mail
Fun Facts
Langley Aerodrome
MAE 2
Lighter-Than-Air
Francois de Rozier and Marquis d'Arlandes rode a free-flight, hot-a
Level Flight Performance
Force Balance
Thrust Required and Available
Power Required and Available
Thrust and Power Minimums
NASA Image
MAE 2
Free Body Diagram
Forces acting on the airplane include:
Lift (L) acts perpendicular to the flight path direction
Basic Aerodynamics
Continuity Equation
Incompressible Flow
Momentum Equation
Euler and Bernoulli
Airspeed Measurement
NASA Image
MAE 2
Stream Tubes and Lines
A stream tube does not have to be bounded by a solid wall.
The natural flow of fluid may be such
Rocket Build Project
Boost Velocity
Terminal Velocity
Max Altitude
Drag Modeling
Flight Testing
MAE 2
Rocket Project
Two-person teams will design, build, and fly a compressed-air launch vehicle.
Use flight test video to validate trajectory predictions.
Pr
Rocket Equation
Rocket Equation
Burnout Velocity
Staging
Maneuver Propellent
NASA Image
MAE 2
Forces Acting on the Rocket
Neglect drag force (for now).
Assume rocket weight is small when compared to the massive engine thrust.
T D Mg=M
T
Mg0
T =M
dV
dt
dV
Orbit Mechanics
The Two-Body Problem
Energy Equation
Specific Momentum
Elliptical Orbit Geometry
NASA Image
MAE 2
The Two-Body Problem
Motion of a spacecraft in the solar system is generally dominated by one central body
at a time.
The trajectory of the s
Materials
Strain
Hooke's Law
Buckling and Deflection
NASA Images
Material Selection
Component Weight
MAE 2
Strain
Strain measures how the material reacts to applied loads.
length=l
F
F
Tension:
l
F
F
Compression:
l
l
l
l=unloaded length
l=change in lengt
Aircraft Propulsion
Propeller Efficiency
Piston Engines
Thrust Equation
Jet Engines
MAE 2
Aircraft Propeller Efficiency
The propeller efficiency is the ratio of power available from the propeller (to move the
airplane) to the power delivered by the engine
MAE 02 Introduction to Aerospace Engineering
Homework Set #1 Due WED 09 OCT 2013
Name: _
ANSWERS: (Turn in only this sheet)
Problem 1.1
a. 3,040 oC
b. 3,227 oC
c.
d.
3,773 oC
6,300 oC
Problem 1.2
a. 0.24 W
b. 134 W
c. 180 W
d. 134 kW
Problem 1.3
a. 47 rad
Aerospace Careers
Choosing a Job
Friendly Advice
FAQ
Aerospace Organizations
Continuing Education
MAE 2
Choosing a Job
Employment choice is a very personal decision that involves many factors:
type of work
technical
management
manufacturing
research lab
t
Level and Gliding Flight Performance
Free Body Diagram
Thrust Required
Minimum Thrust
Thrust Available
Gliding Flight
Maximize Range
NASA Image
MAE 2
Free Body Diagram
Forces acting on the airplane include:
Lift (L) acts perpendicular to the flight path d
MAE 02 Introduction to Aerospace Engineering
Homework Set #3 Due FRI 13 NOV 2015
Name: _
Circle the most correct answer to each of the following questions.
Problem 3.1
a. 0.01
b. 0.2
c. 0.5
d. 0.8
Problem 3.2
a. 30 nmi/hr
b. 50 nmi/hr
c. 85 nmi/hr
d. 100
Aircraft Propulsion
Propeller Efficiency
Piston Engines
Thrust Equation
Jet Engines
MAE 2
Aircraft Propeller Efficiency
The propeller efficiency is the ratio of power available from the propeller (to move the
airplane) to the power delivered by the engine
MAE-02 Introduction to Aerospace Engineering
Practice Set #5
Problem P5.1
The Sopwith Camel has a maximum lift-to-drag ratio of 7.7, aspect
ratio = 4.1, Oswald efficiency factor = 0.7, parasite drag
coefficient (C_D0) = 0.04, mass = 635 kg, and wing area
MAE-02 Introduction to Aerospace Engineering
Practice Set #4
Problem P4.1
The pressure, velocity, and density far ahead (upstream) of an
airfoil are 2116 lb/ft2, 100 mi/hr, and 0.002377 slug/ft3. A
pressure of 2070 lb/ft2 is measured at a point on the air
MAE-02 Introduction to Aerospace Engineering
Practice Set #3
Problem P3.1
A satellite in geosynchronous orbit follows the rotation of the Earth
so that it appears stationary relative to the Earth's surface. What
is the orbital radius for a satellite in ge
MAE-02 Introduction to Aerospace Engineering
Practice Set #2
Problem P2.1
The combustion chamber of a rocket engine has a temperature of 3500 K
and experiences a pressure of 2x106 N/m2. If the pressure at the
nozzle exit is 5x104 N/m2, what is the exit te
MAE-02 Introduction to Aerospace Engineering
Practice Set #1
Problem P1.1
The airspeed of an unladen European Swallow is about 10 m/s. What is
its airspeed in knots (nmi/hr)?
Problem P1.2
The inlet area of a turbojet engine is 7 ft2. What is the inlet are