Fundamentals of Aerodynamics

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Introduction to Aerodynamics of Flight

Basic Aerodynamics

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2. Adobe pdf reader or any pdf reader. Download now.

1st Year: Chapter 4 + Installers

Please download the files located in the folder below. Password is: ae

Note: Download all files and put them in one folder.

Contents:
A. Installers
1. Java
2. Quicktime
3. Shockwave

Chapter 4
1. Movie Clip
2. Java Applets

Read Chapter 4 of your book and practice with the applets contained below. Good Luck and have fun.

We will have a quiz on Friday, July 18, 2008.

How to Download?
1. Enter the password below and hit enter.
2. You will be redirected to another window.
3. Click on the folder that you want to download. When the contents appear, scroll to the left and click on the download icon(a green arrow pointing downwards). When you are prompted to save file, click yes.
4. Repeat step 4 until you have downloaded all the files.
5. For installers, click the downloaded files and follow the instructions to install it to your computer. For the Chapter 4 contents, just click on the files and wait.

5th Yr: Sample Wt. Estimates for Jet Transport

Note: All examples are based on a series of aircraft design books by Dr. Jan Roskam

5th Year: Sample Weight Estimates For 2 Engine Prop Plane

Movie:The Astronaut Farmer

Title: The Astronaut Farmer
Quality: DVDRip-XviD
Year: 2007


Directed by: Michael Polish
Genre: Adventure / Drama
Runtime: 104 min
Country: USA
Starring: Billy Bob Thornton, Virginia Madsen, Bruce Willis, Bruce Dern, Tim Blake Nelson...

Synopsis:

From the time he was a child, Charles Farmer had only one goal: to be an astronaut. Earning his degree in aerospace engineering and joining the Air Force as a pilot, Farmer was a natural for NASA's astronaut training program and was well on his way when a family situation forced him to drop out. But Farmer was not a man to let anything stand in the way of a dream. He spent the next decade and every cent he had building his own rocket in a barn on his ranch in Story, Texas, working toward the day when he could triumphantly launch it into space. By himself. Sharing his vision are his wife Audie and their children daughters Sunshine and Stanley, and 15 year old Shepard, already a budding engineer and eager to serve as "mission control" on the big day.

Watch:
(click the links below to watch movie)
Part 1
Part 2
Part 3
Part 4
Part 5
Part 6

5th yr: Aircraft Design 1,W Estimates

AIRCRAFT DESIGN 1

(note: click on the pictures if they are partly hidden.)

Chapter 1: Aircraft Preliminary Sizing

Required for initial aircraft sizing:

1. Payload and type of payload

2. Range and/or loiter requirements

3. Cruise speed and altitude

4. Field length for take-off and landing

5. Fuel reserves

6. Climb requirements

7. Maneuvering requirements

8. Certification base i.e. experimental, FAR 23, FAR 25, military

Aircraft design parameters to define for Chapter 1:

1. Gross Take-off Weight, W_TO
2. Empty Weight, W_E
3. Mission Fuel Weight, W_F
4. Maximum Required Take-off Thrust, TTO/Take-off Power, P_TO
5. Wing Area, S and Wing Aspect Ratio, A
6. Maximum Required Lift Coefficient (Clean), C_Lmax
7. Maximum Required Lift Coefficient for Take-off, C_LmaxTO
8. Maximum Required Lift Coefficient for Landing, C_LmaxL

Evolution of a Mission Specification and its relation to Preliminary Sizing and Design

I. Estimating Take-off Gross Weight, W_TO, Empty Weight, W_E, and Mission Fuel Weight, W_F

Method for Rapid Estimation of W_TO, W_E, W_F

Applicable to:

1. Homebuilt Propeller Driven Aircrafts
2. Single Engine Propeller Driven Airplanes
3. Twin Engine Propeller Driven Airplanes
4. Agricultural Airplanes
5. Business Jets
6. Regional Turbopropeller Driven Aircrafts
7. Transport Jets
8. Military Trainers
9. Fighters
10. Military Patrol, Bomb and Transport Aircrafts
11. Flying Boats, Amphibious and Float Aircrafts
12. Supersonic Cruise Airplanes

Where:

W_OE/OWE is the airplane operating weight, empty

W_F is the mission fuel weight

W_PL is the payload weight

W_{OE =} W_E + W_tfo + W_crew

Where:

W_E = empty weight

W_tfo = weight of all unusable fuel and oil

W_crew = weight of the crew required to operate the airplane

Sometimes,

W_E = W_ME + W_FEQ

Where,

W_ME = manufacturers empty weight

W_FEQ = fixed equipment weight, this includes: avionics equipments, air conditioning equipment, auxiliary power unit (APU), furnishings and interiors, other equipments essential in the operation of the aircraft.

Steps in determining W_TO, W_E, W_F:

1. Determine the mission payload weight, W_PL
2. Guess a likely value of take-off weight, W_TOguess
3. Determine the mission fuel weight W_F
4. Calculate the tentative value for W_OE from: W_{OE tent}= W_TOguess - W_F -W_PL
5. Calculate a tentative value for W_E from: W_{E tent} = W_{OE tent} - W_tfo- W_crew

Note: at this stage W_TO, = 0.05% or more of the take-off weight, is often neglected.

6. Find the allowable value of W_E

7. Compare the values of W_Etent and for W_E as obtained from steps 5 and 6. Next, make and adjust to the value of W_TOguess and repeat steps 3 through 6. Continue this process until the values of W_Etent and W_E agree with each other to within 0.5%.

II. Determination of Mission Payload Weight, W_PL, and Crew Weight, W_crew

Mission Payload Weight, W_PL usually consists of passenger and baggage, cargo, military loads such as ammunitions, bombs, external tanks, pods, etc. For passenger in a commercial airplane, an average weight of 175 lbs per person and 30 lbs of baggage is assumed for short to medium distance flights and 40 lbs baggage weight per passenger for long distance flights.

Crew Weight, W_crew is calculated based on the following considerations:

Commercial:

The crew consists of the cockpit crew and the cabin crew. The number of people in each crew depends on the airplane and its mission. It depends also to the total number of passenger carried. http://www.risingup.com/fars/info/part91-533-FAR.shtml states the minimum cabin crew per passengers. An average of 175 lbs and 30 lbs for baggage is a reasonable assumption for flight crews.

Military:

200 lbs is assumed per crew because extra gear carried.

Note: For part 23 aircrafts where owners are also pilots, it is not unusual to have the crew weight as part of the payload.

III. Guessing a Value of Take-off Weight, W_TOguess

A guess of the value is based on similar airplanes by comparing their mission specifications. If no reasonable comparison can be made, the you have to make a wise guess.

IV. Determination of Mission Fuel Weight, W_F

W_F = W_{F used} + W_{F res}

Where:

W_{F used} = fuel actually used during the mission

W_{F res} = fuel reserve required for the mission . Refer to FAR Part 21 for min. reserves

An Example of a Mission Profile

Important: The fuel – fraction for each phase is defined as the ration of end weight to begin weight.

Phase 1: The Engine starts and warms-up. Begin weight is W_TO. End weight is W₁. The fuel-fraction for this phase is by definition: W₁/ W_TO . Refer to the table below for values.

Phase 2: Taxi. W2/W1

Phase 3: Take-off. W3/W2

Phase 4: Climb to Cruise altitude and accelerate to cruise speed. W3/W4. However, sometimes it is desirable to calculate the value from:

For propeller – driven airplanes:

Note: V_cl is in mph. Refer to table 2.2 for guidance.

For Jet airplanes:

E_cl = (1/C_j)_cl (L/D)_cl ln(W3/W4)

Note: For C_j refer to table 2.2 for guidance.

Phase 5. Cruise. W5/W4. This ratio can also be estimated from Breguet’s Range Equation.

For Propeller- Driven Airplanes (Note: Rcr is in statute miles = 5280ft)

For Jet Airplanes (note: Rcr is in nautical miles = 6076 ft, usually provided in mission specifications)

Phase 6: Loiter. W6/W5

Phase 7: Descent. W7/W6

Phase 8: Landing, Taxi, and Shut-down. W8/W7.

Calculate Mission Fuel-Fraction, M_ff

M_ff = (W₁/W_TO)x_i=1ⁱ⁼⁷(W_i+1/ W_i)

W_Fused can now be calculated…

W_Fused = (1 - M_ff) W_TO

Mission fuel weight, W_F, can now be calculated.

W_F = W_Fused + W_{F res}

Finding the Allowable value given W_TO for W_E

The values of A and B are provided below:

WARNING:

The primary structure to which the data above is based is constructed from metallic materials. If you wish to obtain an estimate of WE for an airplane which is to be made of composite materials, be guided with the following:

1. Determine which airplane components are to be made from composite materials.
2. Determine an average value for Wcomp/ Wmetal for the new airplane. The allowable value for WE from the data above must now be multiplied by Wcomp/Wmetal.

Keep In Mind: Non-primary structures, such as floors, fairings, flaps, control surfaces, and interior furnishings, have been manufactured from composites for several years back. Claims to saving weight relative from the above data should be made with great caution.

Note:

1. The weight reduction factors above should be used when changing from 100% conventional aluminum to 100%composite construction.
2. For lithium-aluminum alloys used in the fuselage, wing, or empennage, a weight reduction of 5 – 10% may be claimed relative to conventional aluminum alloys.

3rd Year: MATERIALS BOOK

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AE 110: Intro to Aerospace Engineering

Home Work No. 2
Due date: July 11, 2008

Note: click link to download your homework. Answer only Problem Set No. 2.

Download Homework Here


Foil Sim

Access FoilSim here.

Note: You need an Internet connection to access FoilSim. If you choose to work at home without internet connection, download the applet and save it to your own hard drive. FoilSim needs a JAVA plug in to work.

UPDATE! UPDATE! UPDATE! UPDATE!

Paper Plane Design and Construction Book
- Read this great and informational book about the design and construction of paper airplanes. Lots of examples are presented with easy to follow pictorial instructions.

DOWNLOAD HERE