solve this Q in c++ with clearify
2. Problem Statement: Figurel. Wing section (keft) and Fores (righi) Lif (L) is the foree that directly opposes the weight (graviry) of an airplane and holds the aipplane in the air. Mostly the wings gencrate lift (ses figare 1). The amoust of lif generaed by an object depends on a namber of facsors. including the density of the air, the velocity between the object and the air, the viscosity and compressibility of the air, the surface area ever which the air flows, the shape of the body, and the body's inelination to the flow, also called the angle of attack (a). In gencral, the dependence on body shape, inclieation, air viscosity, and compressibility is very complex. One way to deal with complex dependencies is to charaterize the dependence by a single variable. For lift, this variable is called the lift coefficient, designatedCr. For given air conditions, shape, and incliuation of the object, we have to detemaine a value for CI to determine the lift. For seme simple flow conditions and geometries, and low inclinaticas, aerodynamicists can now determibe the valae of Cl mathematically Bot, in meneral, this parameter is deternined experimentally asing models in a wind tunnel. For thin airfoils, at small angles of attack, the lift coefticient is approximately two times =3.14159 times the angle of atlack a sxprtosed in mians: Cl=2pta(inradians) The modem lift equation states that lift L is equal to the lift eoefficient (Cl) times the density of the air () times half of the square of the velocity (V) times the wing area (A). 3. Task: Write a C+ peogram that detemines at what velocity shoeld you be traveling in the F.22 to maintain a 5 . angle of attack at an alritude of 35.000 feet? The F.22 weight is 57.600 pounds and wing area is 830 square feet. The F-22 speed should be indicated in Mowh speed. Moch number is a ratio of the spect of a body (aireraft) to the specu of sound. It is said that the aireaft is flyise at Mach 1 if its speed is equal to the speed of sound in air. An airsaft flying at Mach 2 is flying at twice the speed of sound in air, etc. Important Note: Both air density () and speed of sound depends on the cruising alitule. See the following L.C.A.O. 2 chart A [page 3]. Do not read the data from the kobbeard. but instead we initialization. The angle a is given in [Acegre], the velocity V in [foet per sceond], the arsa of the wings A in (square feet]. and the lift L [in pounds]. Display catput with two decimal places as shown [You can magnify the serees capture in figure 2 below to see the detais]. 4. Sample rua Figure 2. Screen Capture of the Exccution 6. Additional information 1. Chart A: I.C.A.O. Standard Atmosphere Table II. How to convert knots to feet per second [kn to ft/sec]: v[ft/sec]=1.68780986v[kn] How many feet per second in a knot: If v[kn]=1, then v[ft/sec]=1.687809861=1.68780986[ft/sec] How many feet per second in 40 knots: If v[kn]=40 then v[ft/sec]=1.6878098640=67.5123944[ft/sec]
