University of North Texas Horizontal Wind Tunnel Aerodynamic Lab Report

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University of North Texas

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Mechanical Engineering

I am looking for someone to help me with my lab report for my Mechanical engineering class. I will provide with all the information needed for the lab including the lab report format and calculation background. I have attached a general information regarding the report and I will provide you with all the data and further information through the chat.

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α (degrees) 0 5 10 15 20 PD (kPa) 0.65 0.65 0.64 0.59 0.55 FL (N) -17.23 -4.6 6.25 13.37 12.54 FD (N) 5.07 5.41 6.79 10.23 12.42 Sensitivity of Force Measurements: 0.01 N Sensitivity of Pressure Measurements: 0.01 kPa 25 30 35 40 45 50 0.53 0.49 0.43 0.38 0.33 0.26 13.82 17.24 19.51 21.88 22.83 19.56 16.46 19.69 23.38 27.1 30.02 30.35 Lift and Drag - Horizontal Wind Tunnel AF100 UTD Mechanical Engineering Fluids Lab (MECH 3115) Dr. Hui Ouyang How to? To complete your report, you need to: • Water the presentation video. • Watch the experiment video • Complete the quizzes about this experiment. • Perform data analysis • Perform a discussion about your results/findings • Assemble your work and complete the report The University of Texas at Dallas Experimental instruments/apparatus The University of Texas at Dallas AF 100 ❑ AF 100 can expose an object with various geometry to air flow, ultimately to measure drag / lift / moment. ❑ In your experiment, you will use NACA2412 aerofoil, not a golf Fan sucks air from the funnel area ball. Air Flow 4 Theory The University of Texas at Dallas NACA 2412 Aerofoil This experiment measures drag and lift coefficients at multiple different angles of attach, to recognize the relationship among noted variables. Wake formation Air Flow α Tilting angle (angle of attack) Wake formation By Mm.cobos - Own work, CC BY-SA 3.0, https://commons.wikimedia.org/w/index.php?curid=1650 0441 6 NACA 2412 Aerofoil Lift Measure α, and measure FD and FL, and calculate CD & CL Drag Tilting angle (angle of attack) 7 Coefficient Calculation Equations used to determine coefficients: • Drag Coefficient, 𝐶𝑑 : 𝐶𝐷 = 𝐹𝐷 𝑃𝐷 ∗𝐴𝑝 𝐴𝑝 = 𝑐ℎ𝑜𝑟𝑑 ∗ 𝑠𝑝𝑎𝑛 (NACA2412 Airfoil) chord length = 0.152 m span = 0.3 m • Lift Coefficient, 𝐶𝐿 : 𝐶𝐿 = 𝐹𝐿 𝑃𝐷 ∗𝐴𝑝 The University of Texas at Dallas Experimental Objective • Determine the drag and lift coefficients for an airfoil as a function of angle of attack. • Determine the angle of attack corresponding to the onset of stall. The University of Texas at Dallas Experimental Procedure 1. Switch on the power. 2. Lock the AFA3 Three Component Balance (Force Balance) strings (rotate the levers to extreme clockwise end). 3. Change angle of the aerofoil. Start your experiment from zero degrees. 4. Place pitot tube aligned to leading edge of aerofoil. 5. Release the lock of Force Balance strings by rotating the levers half to one turn in anti-clockwise direction. 6. Zero the force and pressure measurements if needed. 7. Start wind tunnel. 8. Note down forces and pressure values from display board/computer. 9. Stop wind tunnel. 10. Repeat steps 2-9 for every 5 degree increment in angle. 11. Switch off the power. Data Collection α PD FD FL 0 5 10 15 20 25 30 35 40 45 50 Data Analysis α PD FD FL CD CL 0 5 10 15 20 25 30 35 40 45 50 Results and Discussion • Plot angle of attack vs coefficients 𝐶𝐿 and 𝐶𝐷 • “Stalling” phenomenon is marked as a decrease in lift coefficient for an increase in angle of attack The University of Texas at Dallas Results and Discussion • Does an increase in angle of attack lead to an increase in drag indefinitely? Lift? • At what angle should an airplane try to lift off at to generate maximum lift for minimum drag? The University of Texas at Dallas The end.
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WIND TUNNEL LAB REPORT

Wind Tunnel Lab Report
Author
University Affiliation

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ABSTRACT
The desire for good aerodynamic characteristics in various airfoil designs has necessitated the
adoption and the use of the numerous researches and engineering testing models in order to
define and improve on their performance. This study focuses on determining the lift and drag
coefficients at various angles of attack. The drag and lift coefficients are determined analytically
used the obtained data. The variation in the coefficient can be accounted by the change in the
angle of attack. This correlation between the angle of attack and the coefficients is
comprehensive discussed herein as well as its effect on the airfoil lift and drag. In pursuit of
establishing and demonstrating the vehement link between the aforementioned parameters,
graphical plots and presentations regarding the lift and drag coefficients at various angles of
attack are utilized.

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INTRODUCTION
Design for good aerodynamic characteristics is one of the most fundamental considerations in
any design of any kind of airfoil. Thus, the phenomenon of the wings of the birds, over time, has
gradually inspired the design of airfoils and consequently triggering numerous studies on the
performance of airfoils. This has served as an impetus for the development of a variety of airfoils
in order to optimize the lift, drag and stalling characteristics over a vast range of speed and
through a variety of fluids.
The numerous studies concerning airfoils has expended the development of various theories such
as the thin airfoil theory, the Bernoulli’s theory of flight, Newton’s theory of light and many
more.
The Bernoulli’s theory of flight is the most commonly deployed theory in the analysis of airfoils
and it states that: for a non-viscous, incompressible fluid in steady flow, the sum of pressure,
potential and kinetic energies per unit volume is constant at any point. Ignoring the potential
energy due to altitude it becomes the Bernoulli’s principle which states: when the velocity of a
fluid increases, its pressure decreases by an equivalent amount to maintain the overall energy [1].

OBJECTIVES
The aim of the experimen...


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