A 2 m diameter satellite dish, with porosity of 0% is shaped as a porous parabolicdish, . It is used in Antarctica where the highest recorded wind speed is 327 km/hr.When winds higher than 100 km/hr are detected, the dish is automatically rotated toface away from the wind. It is mounted on a pole which is 1.7 m long, to the centreof pressure. (The drag force acts through the centre of pressure) Determine themaximum bending stress, during the storm, at the base of the pole due to the dragforce. The pole is solid, with a diameter of 60 mm.At -40 degrees C, the viscosity of air is 1.5E-5 N.s/m^2 and density is 1.52 kg/m^3.

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Answered: A 2 m diameter satellite dish, with…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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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 pitcher throws a baseball without spin with a velocity of 20 m/s. If the ball has a circumference of 225 mm, calcu- late the drag force on the ball in air at 30°C.
An aircraft with symmetric airfoil of wing area 20 m2, flyingwith velocity 60km/hr experiences lift coefficient of 0.8. Considering the aircraft flying at sea level conditions, determine the mass of the aircraft.
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8. A flat plate ( 1.5 m ) long and ( 1.5 m) wide is towed in water ( p = 1000 kg/m and v=1.31 * 10 “ m / s) in the direction of its length at a speed of ( 20 cm /s). Determine; a) The skin frictional drag force on both sides of the plate. b) The boundary layer thickness at the end of the plate.
An aeroplane has a rectangular planform wing with a span of 12 m and a chord of 2 m. The aircraft is flying at cruising speed of 62 m/s at an altitude of 3,200 m. Assume that the skin-friction drag on the wing can be approximated by the drag on a flat plate of the same dimensions at 0° incidence. Calculate the skin-friction drag and the maximum boundary layer thickness assuming (i) a completely laminar flow, and (ii) a completely turbulent flow. Assume μ = 1.63.10-5 N s/m², p = 0.89 kg/m³. Then, calculate the skin-friction drag accounting for transition at Recr= 5.105. What would the drag benefit be if transition was delayed to a Reynolds number of 106? What reduction in a propeller engine power would this imply in the cruise condition, assuming a propeller efficiency of 0.88?
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Choose the most appropriate statement with respect to the pressure distribution of an airfoil. The flow velocities go to zero at the leading and trailing edge points. Upper and lower surface pressures are lower than under free-stream conditions. Upper and lower surface pressures are higher than under free-stream conditions. O Lift is the difference between the lower and upper surface pressures.
Consider the lifting flow over a circular cylinder with a diameter of 0.5 m. The freestream velocity is 25 m/s, and the maximum velocity on the surface of the cylinder is 75 m/s. The freestream conditions are those for a standard altitude of 3 km. Calculate the lift per unit span on the cylinder.
The airfoil section of the wing of the British Spitfire of World War II fame is an NACA 2213 at the wing root, tapering to an NACA 2205 at the wing tip. The root chord is 8.33 ft. The measured profile drag coefficient of the NACA 2213 airfoil is 0.006 at a Reynolds number of 9 × 106. Consider the Spitfire cruising at an altitude of 19000 ft. Assume that μ varies as the square root of temperature. At this velocity and altitude, assuming completely turbulent flow, estimate the skin-friction drag coefficient for the NACA 2213 airfoil, and compare this with the total profile drag coefficient. Calculate the percentage of the profile drag coefficient that is due to pressure drag. (Round the final answer to three decimal places.) The skin-friction drag coefficient for the NACA 2213 airfoil is .

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