![]() Submission Instructions At the completion of this assignment, you should have one MATLAB script file named HW06_LastName_FirstName.mlx that should be submitted to Brightspace. Determine the area A, location of the neutral axis z ˉ and the moment of inertia I using Simpson's 1/3 Rule. Be sure to show the grid and use equal axis lengths for both the x-direction and z-direction so that it is scaled equally and displays the true shape. Plot the airfoil shape using lines only (no markers) and appropriate axis labels. Scale the normalized data such that the chord c is 150 mm. (c.) The data should be imported into the following variables: xu and x 1 x-coordinates of upper ( u ) and lower ( 1 ) surfaces zu and zl z-coordinates of upper ( u ) and lower (1) surfaces 3. Your code should read and store these numbers in variables to be used for importing the data. (b.) The second line contains two values: the number of data points on the upper surface, and the number of data points on the lower surface. Import the coordinates of the airfoil into MATLAB, Your code to perform the import should take into account the following considerations: (a.) The first line contains the name and should be skipped during import. ![]() Download the coordinate file for the Clark Y Airfoil shape from Brightspace. The following detailed instructions should be followed and all steps must be completed to recieve full credit. Assignment Instructions For this assignment, you will write a MATLAB Live Script file that will compute thesection properties for a Clark Y Airfoil with 150 mm chord length by numerical integration using Simpson's 1/3 Rule. The files within the data follow the Lednicer's format which lists points on the upper surface (from leading edge to trailing edge), then points on the lower surface (from leading edge to trailing edge). the measured distance from the leading edge to the trailing edge c = 1 ). ![]() The files contained within the database provide normalized coordinates which describe the shape of the upper Z 11 and lower Z l surfaces of an airfoil with a normalized chord length c (i.e. The calculations require knowledge of the bending stiffness which is a product of the elastic modulus E and the moment of inertia I of the cross-section and typically varies along the span of the wing: Referring to the parameters shown for a typical airfoil shape in Figure 1, one can calculate the area A, location of neutral axis 2, and the moment of inertia I as A = ∫ 0 c d x ε = 2 A 1 ∫ 0 c d x I = 3 1 ∫ 0 c d x An extensive repository of airfoil shapes can be found online such as the UTUC Airfoil Coordinates Database. For structural analysis, one typically is interested in the deflection ar of the wing subjected to external loads such as lift, drag, and self weight in which the wing is treated as a cantilever beam. This is true for both structural analysis as well as aerodynamic analysis. ![]() A typical problem encountered in the aerospace industry is the optimiration of an airfoil design. Figure 2: Example airfoil database file showing Lednicer's format. Doe Date Introduction: Wing Airfoil Section Properties November 15, amsby 1159 pm Figure 1: Airfoil parameters used for section property calculations. ![]()
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