Based on the momentum integral equation calculate the local fric-tional coefficient, Cr, for the following velocity profiles on a flat plate:(a) = 7(a)=u3(b) =7-1끼U.и2"(c) = 27-27³+7'U

1. Momentum Integral Equation: dxd(δ2U∞2)+U∞(dxdδ2)+τw=0 Here, δ2 is the momentum…

Answered: Based on the momentum integral equation…

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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Rain water is flowing through an inclined plane under gravity as shown in figure. A thin layer of thickness h is formed over the plate. An upward wind flow that exerts a shear stress on the upper surface (y = h) of the liquid layer. The wind flow tends to push the rain layer upward while gravity pulls the layer downward Write continuity and and Navier-Stokes equations to model this flow field. (Assume the flow is fully developed) Obtain expressions for the liquid velocity profile, the shear stress distribution, the volume flow rate, and the the expression for the thickness h of the liquid layer for which there is no net volume flow along the roof
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Consider irrotational flow past a stationary sphere of radius R located at the origin. In the limit r→∞, the velocity field v = U2, as in Fig. 8-6 in the book. (a) Calculate the velocity field v assuming potential flow given by v = Vo(r, 0, 0), where the potential can be assumed to be independent of the azimuthal coordinate and vo= 0. Here, since ə rde Ə Ər for large r/R, look for solutions of the form = f(r) cos 0. Assume a no-penetration boundary condition at the surface of the sphere. (b) Calculate the pressure P and the drag force due to pressure. Vr = U cos 0 and Vo = -U sin 0
Please help, I don't know how to do whats being asked. We have never split a flat plate in half for Shear force. Only know how to split the boundary layer from the uniform portion.

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Based on the momentum integral equation calculate the local fric- tional coefficient, Cr, for the following velocity profiles on a flat plate: (a) = 7 (a)= u 3 (b) = 7-1끼 U. и 2" (c) = 27-27³+7' U