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
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