Fluids and Hydraulics Lab ENSC 3231 Pressure Distribution on an Air Foil Fall 2023 Objective Measure and plot the pressure distribution around an airfoil at least for 3 different speeds, find at 0 degrees angle (horizontal) and 2 degrees angle of attack and analyze what kind of errors do you make and discuss about it in your report. Background Cp is the dimensionless number used to understand the surface pressure gradient of wing profiles. You will use the equation shown in Figure 1 and plot the graph shown in Figure 2. Figure 1: Surface pressure gradient 1- As you have calibrated the wind tunnel test section by measuring the air speed at different motor frequencies and plotted a calibration chart in the previous lab. Choose a pitot tube and utilize the same for this lab (TA would fix it for you). 2- Calculate and plot the dimensionless pressure distribution around the airfoil on the y-axis as function of the dimensionless x/c on the x-axis for 3 different airspeeds. Details about the NACA 0012 will be provided to you. 3- Submit a report documenting your findings: Using Font: Times New Roman 12, Line spacing: double. a. Cover page: name, class number