Showing the Lift Equation
in its Y = mX + b Form

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Subject Area: Physics

Grade Level: 11 - 12

National Science Standards:

• Select and apply technology tools for research, information analysis, problem-solving, and decision-making in content learning.
• Investigate and apply simulations in real-world situations.

 Objective:

After reading an explanation from a NASA Web-based textbook, you will demonstrate an understanding of the text by using it, along with FoilSim, to complete an activity that manipulates the lift coefficient equation to solve for lift as a function of angle of attack, and interpret the complete lift equation.

FoilSim is an interactive simulation software package that determines the airflow around various shapes of airfoils. As you change the parameters of airspeed, altitude, angle of attack, thickness and curvature of the airfoil, and size of the wing area, the software calculates the lift. The package was created at NASA Lewis Research Center to illustrate an example of their research.

Macintosh or MS-Windows 3.x, 95, or NT versions of FoilSim are available for downloading off the World Wide Web at FoilSim Download.

Shown below is a screen shot from the program showing the controls and displays. You may change the values of the variables by using the slider or the input box on the left of the slider.

To use the slider:

1. Click the mouse pointer on the arrows at the ends of the slider.
2. Click the mouse pointer anywhere between the slider and the arrow.
3. Drag the slider with the.

To use the input box:

Simply select the value in the input box, key in the new value, and press Enter or Tab when finished. The button on the slider will move corresponding to the value typed in the box.

 

You will study how lift varies with airfoil shape and also angle of attack. Backround information can be found at:

basic lift equation

airfoil shape

angle of attack

You and your partner(s) will be evaluated on the accuracy and completeness of your answers.

Evaluation:

You will demonstrate your understanding and use of the complete lift equation by solving it in its linear form and applying this equation as a function of angle of attack, in graphical form .

Submitted by: Gary Ruschel, Cleveland, Ohio.