1. write a computer program to determine f by any of the methods listed. 2.use the bisection method to solve (dt/dx=0)explain why these methods are not suitable for the almost equivalent problem use c++ , mat cad or mat lab

s//virtualcampus.pupr.edu/bbcswebdav/pid-540519-dt-content-rid-5045222 1/cout p CD 2 virtuakampus,pupr.edu XNew tab WI-1 Favorites ME 30i0.ROOT FINDING PR eLEMS The Colebrook fonnula for fully turbulent flows in smooth pipes relates a friction factor f to the diameter-based pipe Reynols number R. This formula may be written as i /f 1n(R Vf / 2.51) _ 1.1513 = 0 The formula is generally used with R values greater than about 3000 (where f is ap- proximately equal to 0.0435). The value of f decreases as R increases from 3000. Use a calculator or write a computer program to determine f by any of the methods listed. In each case, explain the choice of starting points and other necessary quantities (if any) and obtain a solution such that the left-hand side of the given equation is less than 0.0005 in magnitude The bisection method (R 20,000). * The false-position method (R- 40,000). The Newton-Raphson method (R = 80,000). The secant method (R = 160,000). , , 2 The thickness t of an airfoil in an NACA airfoi family (NACA preceded the National Acronautics and Space Administration) is described by t/T g(x)-2969./x-1.260x-3.516x2 + 2.843x3-1.015x4 The chord extends from the leading edge at (x 0) to the trailing edge at (x l) the T is the nominal maximum thickness. The true maximum thickness f max is slightl larger than T. An airfoil with T equai to 0.15 is shown in Fig. 3-P8 itruhowa imum thiekness ms, slightly Search the web and Windows | o e https// itualcamp- 1 DOLT s//virtualcampus.pupr.edu/bbcswebdav/pid-540519-dt-content-rid-5045222 1/cout p CD 2 virtuakampus,pupr.edu XNew tab WI-1 Favorites ME 30i0.ROOT FINDING PR eLEMS The Colebrook fonnula for fully turbulent flows in smooth pipes relates a friction factor f to the diameter-based pipe Reynols number R. This formula may be written as i /f 1n(R Vf / 2.51) _ 1.1513 = 0 The formula is generally used with R values greater than about 3000 (where f is ap- proximately equal to 0.0435). The value of f decreases as R increases from 3000. Use a calculator or write a computer program to determine f by any of the methods listed. In each case, explain the choice of starting points and other necessary quantities (if any) and obtain a solution such that the left-hand side of the given equation is less than 0.0005 in magnitude The bisection method (R 20,000). * The false-position method (R- 40,000). The Newton-Raphson method (R = 80,000). The secant method (R = 160,000). , , 2 The thickness t of an airfoil in an NACA airfoi family (NACA preceded the National Acronautics and Space Administration) is described by t/T g(x)-2969./x-1.260x-3.516x2 + 2.843x3-1.015x4 The chord extends from the leading edge at (x 0) to the trailing edge at (x l) the T is the nominal maximum thickness. The true maximum thickness f max is slightl larger than T. An airfoil with T equai to 0.15 is shown in Fig. 3-P8 itruhowa imum thiekness ms, slightly Search the web and Windows | o e https// itualcamp- 1 DOLT