Problem 4 – Consider the isentropic flow over an airfoil. The freestream conditions correspond to a standard altitude of 10,000 ft and M„ = 0.82. At a given point on the airfoil, M = 1.0. Calculate P and T at this point. %3D

Long flights at midlatitudes in the Northern Hemisphere encounter the jet stream, an eastward airflow that can affect a plane's speed relative to Earth's surface. If a pilot maintains a certain speed relative to the air (the plane's airspeed), the speed relative to the surface (the plane's ground speed) is more when the flight is in the direction of the jet stream and less when the flight is opposite the jet stream. Suppose a round-trip flight is scheduled between two cities separated by 3200 km, with the outgoing flight in the direction of the jet stream and the return flight opposite it. The airline computer advises an airspeed of 810 km/h, for which the difference in flight times for the outgoing and return flights is 72 min. What jet-stream speed is the computer using?

Problem 04.006 DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS Skip to question   The NACA 4412 airfoil has a mean camber line given by zc=⎧⎩⎨⎪⎪0.25[0.8xc− (xc)2]0.111[0.2+0.8xc− (xc)2]for  0≤xc≤0.4for  0.4≤xc≤1⎫⎭⎬⎪⎪zc⁢={0.25[0.8xc⁢− (xc)2]for  0≤xc≤0.40.111[0.2+0.8xc⁢− (xc)2]for  0.4≤xc≤1}     Problem 04.006.b - Lift coefficient for a NACA 4412 airfoil Using thin airfoil theory, calculate cl when α = 2.4°. (Round the final answer to three decimal places. You must provide an answer before moving on to the next part.)   cl =

Starting from the basic principles, drive an expression to compute the lift coefficient when the free stream Mach number equals (0.8)