Tech-Design
Aerodynamics
Required Worksheets
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3040598120512
Tech-Design
Aerodynamics
Beginning Level
Required Worksheets
Second Printing
2
BEGINNING LEVEL WORKSHEETS
Atmospheric Data Log
Record today’s atmospheric data in the blanks below.
Today’s date
TEMPERATURE
The temperature of the room is _______________ degrees Fahrenheit and
_______________ degrees Celsius.
NOTE: To convert degrees Fahrenheit to degrees Celsius,
use this formula: [(°F - 32) x 5)] ÷ 9.
PRESSURE
The barometric pressure in the room is _______________ inches of mercury (Hg).
HUMIDITY
The relative humidity in the room is _______________ percent.
3
Windspeed Measurement Activity Worksheet
NAME __________________________________ DATE ___________________
Record your answers below:
Wind Speed Adjuster (1 inch) ________ MPH
Wind Speed Adjuster (4 inches) ________ MPH
Wind Speed Adjuster (6 inches) ________ MPH
4
Lift and Bernoulli’s Principle Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
AIRFOIL A
Wind speed: _____________ MPH
Lift meter reading: ____________ grams
Due to the shape of airfoil A, it should not generate any significant lift at any given wind
speed.
AIRFOIL B
Wind speed: _____________ MPH
Lift meter reading: ____________ grams
NOTE: If you measure any positive or negative lift using airfoil B, then the angle of
attack adjustment is not zeroed properly.
Based on your test results, what can you conclude about the aerodynamics of airfoil A
and airfoil B? Which airfoil creates more lift? Record your answer in the space provided.
The airfoil that creates more lift is: ____________________.
5
Drag Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
CAR A
Wind speed: _____________ MPH
Drag meter reading: ____________ grams
CAR B
Wind speed: _____________ MPH
Drag meter reading: ____________ grams
The car that has less drag is: ____________________.
6
Angle of Attack Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
ANGLE OF ATTACK = 0
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +5
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +7.5
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +10
Wind speed: __________ MPH
Lift meter reading: _________ grams
As the angle of attack increases, the lift _____________.
7
Atmospheric Data Summary Report
Using the information from the daily logs, complete the report:
1. Highest temperature was _______________ °F, _______________ °C recorded on
_______________ (date).
2. Lowest temperature was _______________ °F, _______________ °C recorded on
_______________ (date).
3. Average temperature for the time period covered was _______________ °F,
_______________ °C. (Remember to calculate an average, add all the daily
temperature readings and divide by the number of items added.)
4. Highest barometric pressure was _______________ inches of mercury (Hg)
recorded on _______________ (date).
5. Lowest barometric pressure was _______________ inches of mercury (Hg)
recorded on _______________ (date).
6. Average barometric pressure for the time period covered was _______________
inches of mercury (Hg).
7. Highest relative humidity was _______________ percent.
8. Lowest relative humidity was _______________ percent.
9. Average relative humidity for the time period covered was _______________
percent.
10. Was there a wide spread in the various readings or were the readings all within a
small range?
11. Did you see any trends in the log records? If so, what were they?
8
12. Is there a relationship between the various readings? If so, what is it?
13. What effect do you think changes in atmospheric conditions might have in
aerodynamic performance? Explain your answer.
9
Tech-Design
Aerodynamics
Advanced Level
Required Worksheets
10
ADVANCED LEVEL WORKSHEETS
Lift and Drag Coefficients Activity Worksheet
LIFT COEFFICIENT
TUNNEL DATA
The airspeed for the first part of the experiment is
.
LIFT METER READINGS
AIRFOIL A
Angle
(degrees)
Lift
(grams)
Lift
(kg) *
AIRFOIL B
Lift
(grams)
Lift
(kg) *
0
2.5
5
7.5
10
Angle
(degrees)
0
2.5
5
7.5
10
* Divide each value by 1000 to get kilograms.
11
CALCULATING THE LIFT COEFFICIENT
Calculate the lift coefficient for each meter reading by dividing each value by the
dynamic pressure and the surface area.
Dynamic pressure: Calculate the dynamic pressure using ρ = 1.225 kg/m3.
The dynamic pressure is
1
1
ρV 2 = (
2
2
)(
)2 =
.
Where:
ρ = density of air in kilograms per cubic meter.
V = velocity of air in meters per second.
NOTE: V must be in
meters
miles
meters
. To convert
to
sec
hr
sec
multiply by 0.447.
Surface area: Calculate the surface area of each airfoil. Be sure to calculate your
answer in square meters or convert your answer to square meters.
The surface area of Airfoil A is (length x width x 2)
sq. meters.
The surface area of Airfoil B is (length x width x 2)
sq. meters.
LIFT COEFFICIENT
Calculate the lift coefficient for each airfoil at the specified angle of attack. Each reading
is multiplied by a drag factor to eliminate the drag force from the balance.
ANGLE
OF
ATTACK
0
LIFT
READING
(KG)
AIRFOIL A
DIVIDED
BY DYNAMIC
PRESSURE
DIVIDED
BY SURFACE
AREA
EQUALS
LIFT
COEFFICIENT
2.5
5
7.5
10
12
ANGLE
OF
ATTACK
0
LIFT
READING
(KG)
AIRFOIL B
DIVIDED
BY DYNAMIC
PRESSURE
DIVIDED
BY SURFACE
AREA
EQUALS
LIFT
COEFFICIENT
2.5
5
7.5
10
On a single sheet of graph paper, graph your results. Use the x axis (along the bottom)
for angle of attack. Use the y axis (the vertical axis on the left) for coefficient of lift. Use
a different color pen or pencil for each model tested in the wind tunnel. Don’t forget to
put a key on your graph which tells which color represents what model.
DRAG COEFFICIENT
Calculate the drag coefficient of each of the two cars using the table provided.
DRAG
METER
READING
DIVIDED BY
DYNAMIC
PRESSURE
DIVIDED BY
SURFACE AREA
CAR 1
.00204 m2
CAR 2
.00169 m2
EQUALS DRAG
COEFFICIENT
13
Sample Data – Lift and Drag Coefficient Activity
LIFT METER READINGS (Wind Speed 35 mph)
Angle
(degrees)
0
2.5
5.0
7.5
10.0
Airfoil A
Lift
(grams)
0
22
44
65
81
Lift
(kg)
0
.022
.044
.065
.081
Angle
(degrees)
0
2.5
5.0
7.5
10.0
Dynamic Pressure: ½ ρV2 = 0.5 (1.225)(15.645)2 = 150
Airfoil B
Lift
(grams)
27
46
67
90
112
Lift
(kg)
.027
.046
.067
.090
.112
kg
m • s2
SURFACE AREA
Airfoil A
LxWx2
(.127) (.0762) (2) = 0.0194 m2
Airfoil B
LxWx2
(.127) (.0825) (2) = 0.0210 m2
COEFFICIENTS OF LIFT (calc)
Airfoil A
Angle (degrees)
0
2.0
5.0
7.5
10.0
CL
0
0.00756
0.01512
0.02234
0.02784
Airfoil B
Angle (degrees)
0
2.5
5.0
7.5
10.0
CL
0.00857
0.01460
0.02127
0.02857
0.03556
CONVERSION OF MILES PER HOUR TO METERS PER SECOND
1 mi
5280 ft 12 in.
1 meter
1 hr
meters
x
x
x
x
= 0.447
hr
mi
ft
39.37 in. 3600 s
s
mi
meters
x 0.447 =
hr
sec ond
NOTE: Student data will vary.
14
Zero Lift Angle of Attack Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
ANGLE OF ATTACK:
______ degrees
LIFT METER READING: ______ grams
The zero lift angle of attack is ________.
15
Airfoil Design Worksheet
NAME __________________________________ DATE ___________________
Record the important facts about your airfoil in the spaces provided.
What will your airfoil be used for?
________________________________________________________________
________________________________________________________________
________________________________________________________________
________________________________________________________________
________________________________________________________________
________________________________________________________________
Will the leading edge be blunt or sharp?
________________________________________________________________
Will your airfoil be symmetrical or asymmetrical?
________________________________________________________________
If it is cambered, will the camber be positive or negative?
________________________________________________________________
How long will the chord be?
________________________________________________________________
What will the maximum thickness be and where will it occur?
________________________________________________________________
16
Viscosity Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
The water took _______ seconds to drain out of the tube.
The oil took _________ seconds to drain out of the tube.
Which fluid has the higher viscosity? ______________________ .
17
Tech-Design
Aerodynamics
Comprehensive Level
Required Worksheets
18
COMPREHENSIVE LEVEL WORKSHEETS
Atmospheric Data Log
Record today’s atmospheric data in the blanks below.
Today’s date
TEMPERATURE
The temperature of the room is _______________ degrees Fahrenheit and
_______________ degrees Celsius.
NOTE: To convert degrees Fahrenheit to degrees Celsius,
use this formula: [(°F - 32) x 5)] ÷ 9.
PRESSURE
The barometric pressure in the room is _______________ inches of mercury (Hg).
HUMIDITY
The relative humidity in the room is _______________ percent.
19
Windspeed Measurement Activity Worksheet
NAME __________________________________ DATE ___________________
Record your answers below:
Wind Speed Adjuster (1 inch) ________ MPH
Wind Speed Adjuster (4 inches) ________ MPH
Wind Speed Adjuster (6 inches) ________ MPH
20
Lift and Bernoulli’s Principle Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
AIRFOIL A
Wind speed: _____________ MPH
Lift meter reading: ____________ grams
Due to the shape of airfoil A, it should not generate any significant lift at any given wind
speed.
AIRFOIL B
Wind speed: _____________ MPH
Lift meter reading: ____________ grams
NOTE: If you measure any positive or negative lift using airfoil B, then the angle of
attack adjustment is not zeroed properly.
Based on your test results, what can you conclude about the aerodynamics of airfoil A
and airfoil B? Which airfoil creates more lift? Record your answer in the space provided.
The airfoil that creates more lift is: ____________________.
21
Drag Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
CAR 1
Wind speed: _____________ MPH
Drag meter reading: ____________ grams
CAR 2
Wind speed: _____________ MPH
Drag meter reading: ____________ grams
The car that has less drag is: ____________________.
22
Angle of Attack Worksheet
NAME __________________________________ DATE ___________________
Record your results below:
ANGLE OF ATTACK = 0
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +5
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +7.5
Wind speed: __________ MPH
Lift meter reading: _________ grams
ANGLE OF ATTACK = +10
Wind speed: __________ MPH
Lift meter reading: _________ grams
As the angle of attack increases, the lift _____________.
23
Atmospheric Data Summary Report
Using the information from the daily logs, complete the report:
14. Highest temperature was _______________ °F, _______________ °C recorded on
_______________ (date).
15. Lowest temperature was _______________ °F, _______________ °C recorded on
_______________ (date).
16. Average temperature for the time period covered was _______________ °F,
_______________ °C. (Remember to calculate an average, add all the daily
temperature readings and divide by the number of items added.)
17. Highest barometric pressure was _______________ inches of mercury (Hg)
recorded on _______________ (date).
18. Lowest barometric pressure was _______________ inches of mercury (Hg)
recorded on _______________ (date).
19. Average barometric pressure for the time period covered was _______________
inches of mercury (Hg).
20. Highest relative humidity was _______________ percent.
21. Lowest relative humidity was _______________ percent.
22. Average relative humidity for the time period covered was _______________
percent.
23. Was there a wide spread in the various readings or were the readings all within a
small range?
24. Did you see any trends in the log records? If so, what were they?
24
25. Is there a relationship between the various readings? If so, what is it?
26. What effect do you think changes in atmospheric conditions might have in
aerodynamic performance? Explain your answer.
25
Lift and Drag Coefficients Activity Worksheet
LIFT COEFFICIENT
TUNNEL DATA
The airspeed for the first part of the experiment is
.
LIFT METER READINGS
AIRFOIL A
Angle
(degrees)
Lift
(grams)
Lift
(kg) *
AIRFOIL B
Lift
(grams)
Lift
(kg) *
0
2.5
5
7.5
10
Angle
(degrees)
0
2.5
5
7.5
10
* Divide each value by 1000 to get kilograms.
26
CALCULATING THE LIFT COEFFICIENT
Calculate the lift coefficient for each meter reading by dividing each value by the
dynamic pressure and the surface area.
Dynamic pressure: Calculate the dynamic pressure using ρ = 1.225 kg/m3.
The dynamic pressure is
1
1
ρV 2 = (
2
2
)(
)2 =
.
Where:
ρ = density of air in kilograms per cubic meter.
V = velocity of air in meters per second.
NOTE: V must be in
meters
miles
. To convert
to
sec
hr
meters
multiply by 0.447.
sec
Surface area: Calculate the surface area of each airfoil. Be sure to calculate your
answer in square meters or convert your answer to square meters.
The surface area of Airfoil A is (length x width x 2)
sq. meters.
The surface area of Airfoil B is (length x width x 2)
sq. meters.
LIFT COEFFICIENT
Calculate the lift coefficient for each airfoil at the specified angle of attack. Each reading
is multiplied by a drag factor to eliminate the drag force from the balance.
ANGLE
OF
ATTACK
0
LIFT
READING
(KG)
IRFOIL A
DIVIDED
BY DYNAMIC
PRESSURE
DIVIDED
BY SURFACE
AREA
EQUALS
LIFT
COEFFICIENT
2.5
5
7.5
10
27
ANGLE
OF
ATTACK
0
LIFT
READING
(KG)
AIRFOIL B
DIVIDED
BY DYNAMIC
PRESSURE
DIVIDED
BY SURFACE
AREA
EQUALS
LIFT
COEFFICIENT
2.5
5
7.5
10
On a single sheet of graph paper, graph your results. Use the x axis (along the bottom)
for angle of attack. Use the y axis (the vertical axis on the left) for coefficient of lift. Use
a different color pen or pencil for each model tested in the wind tunnel. Don’t forget to
put a key on your graph which tells which color represents what model.
DRAG COEFFICIENT
Calculate the drag coefficient of each of the two cars using the table provided.
DRAG
METER
READING
DIVIDED BY
DYNAMIC
PRESSURE
DIVIDED BY
SURFACE AREA
CAR 1
.00204 m2
CAR 2
.00169 m2
EQUALS DRAG
COEFFICIENT
28
Sample Data – Lift and Drag Coefficient Activity
LIFT METER READINGS (Wind Speed 35 mph)
Angle
(degrees)
0
2.5
5.0
7.5
10.0
Airfoil A
Lift
(grams)
0
22
44
65
81
Lift
(kg)
0
.022
.044
.065
.081
Angle
(degrees)
0
2.5
5.0
7.5
10.0
Dynamic Pressure: ½ ρV2 = 0.5 (1.225)(15.645)2 = 150
Airfoil B
Lift
(grams)
27
46
67
90
112
Lift
(kg)
.027
.046
.067
.090
.112
kg
m • s2
SURFACE AREA
Airfoil A
LxWx2
(.127) (.0762) (2) = 0.0194 m2
Airfoil B
LxWx2
(.127) (.0825) (2) = 0.0210 m2
COEFFICIENTS OF LIFT (calc)
Airfoil A
Angle (degrees)
0
2.0
5.0
7.5
10.0
CL
0
0.00756
0.01512
0.02234
0.02784
Airfoil B
Angle (degrees)
0
2.5
5.0
7.5
10.0
CL
0.00857
0.01460
0.02127
0.02857
0.03556
CONVERSION OF MILES PER HOUR TO METERS PER SECOND
1 mi
5280 ft 12 in.
1 meter
1 hr
meters
x
x
x
x
= 0.447
hr
mi
ft
39.37 in. 3600 s
s
mi
meters
x 0.447 =
hr
sec ond
NOTE: Student data will vary.
29