Activity 1.2.6 Airfoil Simulation
Introduction
Airfoils have a complex geometry designed to direct airflow. This velocity change
results forces that affect aircraft performance. This can be simulated using a
computer to provide an estimate of expected performance.
In this activity you will design an airfoil to meet the design criteria.
Equipment
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PC with Internet access or FoilSim III Student Version 1.4d software
Engineering notebook
Pencil
Procedure
1. Start the PC and launch the FoilSim applet or FoilSim online version which can
be found at http://www.grc.nasa.gov/WWW/K-12/airplane/foil3.html.
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2. Design the airfoil to achieve the results given by your teacher.
a. Use the geometry assigned by your teacher eg. symmetric, high center,
flat plate, flat bottom, negative camber, ellipse or curve plate.
b. Change the Lift and Drag to Cl and Cd to compare results.
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c. Your airfoil shape results can be seen graphically using the gauges button
as shown below. The final quantitative results are available using the Data
tab.
3. Set the First Angle of Attack to -20O and the Final Angle of Attack to 20O and the
Angle of Attack Step to 5O. Record the Cl and Cd for each angle of attack.
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Conclusion
1. What parameters impact the Cl and Cd?
The wings of the aircraft impact the coefficient of lift and drag.
2. Explain why these have such an impact.
The shape of the wings effect the cl and cd. The wing must be able to slice threw
the air but have enough drag to stay in flight. The shape of the wing completely
dictates that.
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