**75. ssm A uniform rectangular plate is hanging vertically downwardfrom a hinge that passes along its left edge. By blowing air at 11.0 m/sover the top of the plate only, it is possible to keep the plate in a horizon-tal position, as illustrated in part a of the drawing. To what value shouldthe air speed be reduced so that the plate is kept at a 30.0° angle with re-spect to the vertical, as in part b of the drawing? (Hint: Apply Bernoulli'sequation in the form of Equation 11.12.)AMoving air130.0HingeEdge view of plate(a)(b)

Consider the diagram shown below for the horizontal position of plate. Here, FP is the pressure…

Answered: **75. ssm A uniform rectangular plate…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Vr014 Assuming that the velocity distribution in the boundary layer is given by -- y V If a certain section, free stream velocity V was observed to be 10 m/sec and the thickness of the boundary layer as 2.5 cm, then the power loss per unit length due the formation of milli Watt boundary layer is meter (Take p= 0.125 kg/m?)
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A light aircraft is flying at an altitude of 1000 m. If the wing chord is 1.5 m, and the freestream velocity is determined using the equivalent airspeed of 80 m/s, determine the overall Reynold's Number. Also, determine the coefficient of skin friction drag. (*Tip, determine what time of flow it is based on the calculated RN, then choose the correct Cf formula - laminar or turbulent)
Air at 20°C and 1 atm flow past the flat plate in Fig.under laminar conditions. There are two equally spacedpitot stagnation tubes, each placed 2 mm from the wall.The manometer fluid is water at 20°C. If U = 15 m/s andL = 50 cm, determine the values of the manometer readingsh1 and h2, in mm.
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Pu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa
PART A -5 For Air Assume: v=1.46×10 m²/s and p =1.225 kg/m³ Question A1 A flat plate with unit width is placed in a uniform steady two-dimensional flow of air with negligible pressure gradient. The velocity distribution of the boundary layer forming on either side of this plate has been given as: U /Us = 2.0(y/ 8) - (y/8)2.0, where U = 10 m/s. 1- Find and expression for the boundary layer thickness as a function of Rex. 2- At x=1.0 m calculate the shear stress corresponding to the points y=0.0,3.0 and 10.0 mm. 3- Calculate the boundary layer displacement and momentum thicknesses at x=1.0m. By using the calculated momentum thickness determine the drag force acting on one side of the plate between its leading edge and x = 1.0m. 4- At x=1.0m, calculate the mass flow rate through the boundary layer (mkg/s per unit width of the plate). What is the corresponding mass flow rate if the flow was inviscid (m; kg/s per unit width of the plate)? 5- By using appropriate equation (s) explain how the…
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B2 is flying at an altitude of 43,000 ft and a speed of 400 KTAS under standard atmospheric conditions. If the average aerodynamic chord is 39,6 ft, calculate the Reynolds number and the average % aerodynamic chord present on the wing
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Assume velocity distribution in laminar boundary layer over flat plate to follow the law. u/U= sin(ny/28) obtain expressions 8/0 and 8/x. 25

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