ASE 120K - Lab 1 - Test section set up Tufts assembled to...

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Unformatted text preview: Test section set up Tufts assembled to airfoil e of attack at 18 degrees and Reynolds number of 40,000 of attack at 0 degrees and Reynolds number of 40,000 Table 1 Drag Profile of a NACA 0012 Airfoil Drew Rosecrans, DCR544 ASE – 120K Low-Speed Aerodynamics Laboratory The University of Texas at Austin Department of Aerospace Engineering and Engineering Mechanics Spring, 2010 TABLE OF CONTENTS ABSTRACT page # INTRODUCTION page # APPARATUS & PROCEDURE page # RESULTS & DISCUSSION page # SUMMARY & CONCLUSIONS page # APPENDICES page # REFERENCES page # ABSTRACT Both qualitative and quantitative measurements were taken the wake profile of a symmetric airfoil, the NACA 0012. The purpose was to gain an understanding of the airflow around a very simple airfoil and to calculate the coefficient of drag at a zero degree angle of attack with a Reynolds number of 150,000. It was witnessed that the angle of attack with which flow separation occurred at increased as the Reynolds number increased. Also once the flow was separated, in order to reattach it required at lower angle of attack at which it separated. Through measuring the velocity distribution in the wake profile, it was possible to calculate the coefficient of drag to within 3 percent of which NACA claims. The coefficient of drag was found to be 0.0106. INTRODUCTION We are studying the wake velocity profile of a NACA 0012 airfoil for the purpose of understanding the airflow and finding the coefficient of drag via the velocity wake profile. It is necessary to understand the wake of a simple airfoil in order to understand the wakes of more complicated airfoils. The NACA 0012 is a very basic airfoil. It is not cambered as can be taken from the 00 in the name which relates to camber. Now the 12 in the name means that the max thickness of the airfoil is 12 percent the length of the chord. Even though the NACA 0012 is a very simple symmetric airfoil doesn’t mean that it is not useful. In fact it is very commonly used on helicopter, so our experiment does have real world applications. 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 is 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 useful in understanding the general concept of the flow while it is attached to the airfoil and when it is separated. €...
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This note was uploaded on 09/18/2011 for the course ASE 120K taught by Professor Staff during the Spring '10 term at University of Texas.

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ASE 120K - Lab 1 - Test section set up Tufts assembled to...

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