Problem 1: The mid-wing type configuration of the USAF F-16c wing (see Figure la
ID: 3818007 • Letter: P
Question
Problem 1: The mid-wing type configuration of the USAF F-16c wing (see Figure la), can be idealized as a cantilever beam with a uniformly distributed load, that accounts for the weight of the wing as given in Figure 1b. The cantilever deflects under the action of the distributed load, as given in eqn. 1 with a slope as given in eqn. 2. VY Figure 1: (a) USAF F-16c (b) Dimensions and loading conditions of a cantilever beam and its cross-section Deflection and Slope of the cantilever (6L' (1) 24EI wor (3L (2) 6EI where 6(z) and 0(z) are the deflection and slope respectively at location z of the cantilever beam of span Lo, w is the distributed load, E is the Young's Modulus of the material of the beam and I is the area, bh moment of inertia of the rectangular cross-section given as 12 a. Develop a C++ program that prompts the user for the input values and the output displayed on the screen in a tabular form as given in Table 1. The program should first display information regarding the assignment and its purpose along with your identity, before prompting the user for the input. The program should also have two functions Beam-Deflection, and Beam-Slope that will calculate the deflection and slope respectively. 12 Points b. Draw a detailed flow chart on how this program is designed, indicating the necessary inputs, outputs and the algorithm you use. The flow chart should be included as a document file along with your program listing (source code). In the same document file, prepare a help section that documents theExplanation / Answer
Please find the program below:
return ((wO*x*x/24*E*I)*(6*L*L-4*L*x+x*x));
}
return ((wO*x/6*E*I)*(3*L*L-3*L*x+x*x));
}