Perform three iterations of the Newton-Raphson method to determine the root of Eq. (E7.1.1). Use the parameter values from Example 7.1 along with an initial guess of t = 3 s.
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Textbook Solutions for Applied Numerical Methods W/MATLAB: for Engineers & Scientists
Question
The total drag on an airfoil can be estimated by D = 0.01 V2 + 0.95 W V 2 Friction Lift where D = drag, = ratio of air density between the flight altitude and sea level, W = weight, and V = velocity. As seen in Fig. P7.33, the two factors contributing to drag are affected differently as velocity increases. Whereas friction drag increases with velocity, the drag due to lift decreases. The combination of the two factors leads to a minimum drag. ( (a) If = 0.6 and W = 16,000, determine the minimum drag and the velocity at which it occurs. (b) In addition, develop a sensitivity analysis to determine how this optimum varies in response to a range of W = 12,000 to 20,000 with = 0.6.
Solution
The first step in solving 7 problem number 33 trying to solve the problem we have to refer to the textbook question: The total drag on an airfoil can be estimated by D = 0.01 V2 + 0.95 W V 2 Friction Lift where D = drag, = ratio of air density between the flight altitude and sea level, W = weight, and V = velocity. As seen in Fig. P7.33, the two factors contributing to drag are affected differently as velocity increases. Whereas friction drag increases with velocity, the drag due to lift decreases. The combination of the two factors leads to a minimum drag. ( (a) If = 0.6 and W = 16,000, determine the minimum drag and the velocity at which it occurs. (b) In addition, develop a sensitivity analysis to determine how this optimum varies in response to a range of W = 12,000 to 20,000 with = 0.6.
From the textbook chapter Optimization you will find a few key concepts needed to solve this.
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