Problem 5. Air flows at a velocity of U = 20 m/s over a flat bottomed, two-dimensional object with a chordlength of c = 1.0 m and wing span of 6 = 5.0 m as shown. The shape of the object, y = f(x), and thepressure distribution. p = g(x), measured in a wind tunnel with air at STP along the top surface are given in thetable. (a) Calculate and plot the pressure coefficient, C, versus * for the top of the object. (b) Calculate the liftcoefficient, Cr, using the calculated Co. (c) Calculate the lift for the object for these conditions and at a standardcruising altitude of 10 km (assuming constant C₂).UPooI** = x/cy* = y/cp-Pro (Pa)0.0000.00002450.0250.0372140.0500.0530-1270.0750.0648-1520.1000.0743-1510.2000.0992-1540.3000.1114-1660.4000.1149-1740.5000.1045-1740.6000.0911-1050.7000.0646-330.8000.0362260.9000.0126651.0000.000085

Step 1:FormulaeThe coefficient of pressure can be calculated using,…

Answered: Problem 5. Air flows at a velocity of U…

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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A thin wing with a parabolic chord distribution is flying at speed U∞ and zero angle of attack, asshown below. The fluid has density ρ and viscosity μ. Assume that the flow starts laminar at theleading edge but then transitions to tubulent at xcrit = 0.25a. a) Sketch the regions of laminar and turbulent flow over the wing. Calculate and label relevantdistances.b) Determine the drag force, D, and the drag coefficient, CD ≡ D/((1/2) ρU2∞S), where S is theplanform area of the wing. Express your drag coefficient answer in terms of the Reynoldsnumber based on a, Rea ≡ (U∞a)/nu.
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Subject: Fluid Dynamics Find the lift force of potential flow a half cylinder. please help me check my solution and verify the answer.
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