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- 1. A flat plate airfoil with a chord length of 1 m and a width of 6 m is required to generate a lift of 40, 000 N when flying in air at a Mach number of 2.0, a temperature of −20°C and a pressure of 105 P a. What is the required angle of attack? What is the wave drag at this angle of attack? 2. A symmetrical diamond-shaped airfoil is placed at an angle of attack of 2° in a flow at Mach 2 and static pressure of 2×103 P a. The half-angle at the leading and trailing edges is 3° . If its total surface area (top and bottom) is 4 m2 , find the forces due to lift and wave drag acting on the airfoil.A horizontal-axis wind turbine with rotor 80m in diameter is 35% efficient in 18m/s wind at 0.977 atmospheric pressure and 25°C. a. Calculate the total amount of power the wind turbine would produce in those winds. b. Estimate the amount of power the turbine would produce if the altitude increased by 1500m and the temperature increased to 30°C. TABLE 6.1 Density of Dry Air at a Pressure of 1 Atmosphere Temperature Temperature Density Density Ratio (°C) (°F) (kg/m³) (KT) -15 ៦ ៩៩ ៨ ៩ t = w c! ម៉ត់ -10 5 15 5.0 14.0 23.0 32.0 41.0 50.0 59.0 68.0 77.0 86.0 95.0 104.0 1.368 1.342 1.317 1.293 1.269 1.247 1,225 1.204 1.184 1.165 1.146 1.127 1.12 1.10 1.07 1.05 1.04 1.02 1.30 0.98 0.97 0.95 0.94 0.92 "The density ratio Kr is the ratio of density at 7 to the density at the standard (boldfaced) 15°C. TABLE 6.2 Air Pressure at 15°C as a Function of Altitude Altitude (meters) 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 Altitude (feet) 0 656 1312 1968 2625 3281 3937 4593 5249 5905 6562…2. Air at 40 °C moves over a long flat plate with a uniform free stream velocity of U = 900 m/s. Assume the boundary layer formed above the surface of the plate starts at the tip of the leading edge and the velocity profile inside the boundary layer has power-law form as Re, <107 8 10' < Re, <10* 7 - (). for u SxAir flow across a cooling fin: A 35 mm (in the streamwise direction) aluminum cooling fin has a temperature of 54 C and needs to be cooled to 44 C using cross flow. The fin is surrounded by air and must be cooled with laminar flow to minimize the boundary layer thickness and reduce aerodynamic drag. 1. What is the fastest fluid velocity that can be used to keep the flow laminar? 2. If the flow velocity drops 10% and the frictional force is decreased by 20%, by what percentage would you expect the heat transfer to drop?Q1 A car is traveling at sea level at a constant speed. It weighs 2500-lbs, has a frontal area of 20 ft² and has a 90% drivetrain efficiency. Its engine runs at 4000 rev/min, producing 168 ft-lb of torque. The drive axle slippage of 2%, 14-inch-radius wheels, and an overall gear reduction ratio of 2.5 to 1. What is its drag coefficient?Problem 1. A smooth plate with length L = 3.0 m and width b = 0.90 m moves through still air at STP at a velocity of U = 4.5 m/s that is aligned with L. Calculate the following for a boundary layer that stays laminar and for one that trips to turbulent at the leading edge: (a) boundary layer disturbance thickness, 8, at x = 0.5, 1.0, 1.5, 2.0, 2.5, and 3.0 m from the leading edge of the plate, (b) wall shear stress, Tw, at those æ- locations, and (c) friction drag, Fp.f, on one side of plate. (d) Calculate percent decrease in drag for laminar versus turbulent boundary layer.A 0.5 m x 2 m flat plate is towed at 5 m/s on a 2-mm-thick layer of SAE-30 oil at 38°C that separates it from a flat surface. The velocity distribution between the plate and the surface is assumed to be lincar. What force is required if the plate and surface are horizontal? 1.4Consider that you are in an area of Seattle where the wind is blowing at 40 km/h with a temperature of 0 ° C. If you can be mathematically modeled as a cylinder with diameter external of 0.3m and height of 1.70 m. Calculate the number of hot dogs that you need to eat to make up for the amount of energy you lose in heat form for an hour. Note 1: Consider that the external temperature of the clothes is kept constant at 25 ° C. Note 2: Consider a 150 kcal hot dog.An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. wWw wwProblem 3. Air at 20°C and 1 atm (p= 1.2 kg/m³ and µ= 1.8×10¹5 kg/(m-s)) flows at 3 m/s past a sharp flat plate 2 m wide and 1 m long. Determine: a) the boundary layer thickness and the wall shear stress at the end of the plate b) the air velocity at a point 4.5 mm normal to the end of the plate c) the total friction drag on both sides of the plate5) A wedge airfoil is placed in a supersonic flow at M = 2. G. Calculate the lift and drag coefficients at 4° angle of attack. Hint: Consider the free-stream pressure at the base of the airfoil. 4° PooCompute the lift and drag coefficients for a symmetric, diamond-shaped airfoil with a thickness-to-chord ratio t/c equal to 0.10, flying at Mach 3.5 in air (y=1.4) at zero angle of attack. M₂ - 3.5SEE MORE QUESTIONS