Riemann sum excel

WVU Fundamentals of Engineering Program Fall 2019 ENGR 101: Engineering Problem Solving I Excel Riemann Sum Analysis Problem The cross-section of an aircraft wing is commonly referred to as an airfoil. Many airfoils were initially designed by the National Advisory Committee for Aeronautics (NACA), the government agency that went on to became NASA. One of the airfoil families developed by this agency is known as the 4 digit series, which has some symmetric (dimensions for the top surface and bottom surface are the same) airfoils that fit the following relationship for the Upper and Lower Surfaces of the airfoil. In the equation, t represents the maximum thickness of that particular airfoil and is traditionally between 6 and 30 percent of the total width of the airfoil, also known as the chord length, c. This thickness needs to be entered as a fraction of the chord length, typically between 0.06 and 0.30. ± 𝑦 𝑡 𝑥 𝑥 𝑥 2 𝑥 3 𝑥 4 = (0.29690√ − 0.12600 − 0.35160 ( ) + 0.28430 ( ) − 0.10150 ( ) ) 𝑐 0.20 𝑐 𝑐 𝑐 𝑐 𝑐 Equation 1 On most aircraft, the wings also serve as a major fuel tank on the plane. By making two assumptions, first that since the airfoil is symmetric the volume on the lower half of the airfoil is equal to that of the upper half of the airfoil, thus the area between the line y=0, 𝑦 and the upper surface (+ ) can be doubled to get the total area between the upper and lower surfaces of the airfoil. The second 𝑐 assumption is that the wing has the same cross-section for the uniform depth of 5 meters. Thus, the volume inside the airfoil can be estimated by using the area found from a Riemann Sum from the cross section times the depth of 5 meters. A step by step listing of tasks that is to be completed is provided for your success on this assignment. 1. Open EXCEL and save the file as “Wing Volume Analysis ENGR101_#$%_Lastname_Firstname.xlsx” where #$% is the three character section number of your ENGR 101 course. 2. Create a new sheet in the file and name it “Data” 3. In the Data Sheet Create a. An area for input values of Thickness, Chord length, and Depth at the top of the sheet (Rows 1 thru 3) assign values of 0.20 for thickness, 3 meters for the chord length, and 5 meters for the depth for the wing fuel tank. b. In Row 5 Create Column Headings of “X/C”, “Y/C”, “X”, “Y”, “Area” c.