Introduction - I NTRODUCTION The wake velocity profile of a...

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INTRODUCTION The wake velocity profile of a NACA 0012 airfoil can be used to find the coefficient of drag for the airfoil. Also it is necessary to understand the wake of a simple airfoil, like the NACA 0012, in order to understand the wakes of more complicated airfoils. It might be useful to introduce common components of airfoils that will be used. Figure 1 shows all of the different aspects of airfoils. include alpha Figure 1 The NACA four digit series is a very common way of describing an airfoil. Let’s use another airfoil to understand the nomenclature. Take the NACA 2314 for example, the first digit represents the max camber of the airfoil as a percentage of the chord. So for this airfoil the max camber is 2% of the chord. The second digit represents the position of max camber in tenths of the chord. For this airfoil the max camber occurs at 3/10 of the chord from the leading edge. The last two digits represent the maximum thickness of the airfoil in percent of the chord. In the NACA 2314 the maximum thickness of the airfoil is 14% of the chord (Reference here). Given this it is easy to see that the NACA 0012 is a symmetric airfoil because it doesn’t have any camber. Although the NACA 0012 is a very simple airfoil, it has many applications. It is used on many helicopters because of the fact that it is symmetric (Reference here).
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There is going to be a qualitative and quantitative part of this experiment. The qualitative part will all be flow visualization. The flow visualization techniques that will be used are a smoke wire and tufts on the top of the airfoil. These two techniques will be explained later in the apparatus and procedures section. They are
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This note was uploaded on 09/18/2011 for the course ASE 120K taught by Professor Staff during the Fall '10 term at University of Texas at Austin.

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Introduction - I NTRODUCTION The wake velocity profile of a...

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