Consider an incompressible flow, laminar boundary layer growing along the surface of a flat plate, with chord length c, as shown in Figure 1. 4 Streamline upper boundary of control volume Velocity profile (y) Edge of boundary layer Figure 1 For an incompressible, laminar, flat plate boundary layer, the boundary-layer thickness & at the trailing edge of the plate is 8 5 VRe and the skin friction drag coefficient for the plate is D quC(1) * yRe. where the Reynolds number is based on chord length 1.328 Re = Hoo Assuming that the velocity profile through the boundary layer is given by a power-law variation u- Voo Calculate the value of n, consistent with the information given above.
Consider an incompressible flow, laminar boundary layer growing along the surface of a flat plate, with chord length c, as shown in Figure 1. 4 Streamline upper boundary of control volume Velocity profile (y) Edge of boundary layer Figure 1 For an incompressible, laminar, flat plate boundary layer, the boundary-layer thickness & at the trailing edge of the plate is 8 5 VRe and the skin friction drag coefficient for the plate is D quC(1) * yRe. where the Reynolds number is based on chord length 1.328 Re = Hoo Assuming that the velocity profile through the boundary layer is given by a power-law variation u- Voo Calculate the value of n, consistent with the information given above.
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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Transcribed Image Text:Consider an incompressible flow, laminar boundary layer growing along the surface of
a flat plate, with chord length c, as shown in Figure 1.
4.
Streamline upper
boundary of
control volume
Velocity profile
(y)
Edge of boundary layer
Figure 1
For an incompressible, laminar, flat plate boundary layer, the boundary-layer
thickness & at the trailing edge of the plate is
and the skin friction drag coefficient for the plate is
D'
1.328
qoC(1) VRe.
where the Reynolds number is based on chord length
PooVool
Rec =
Hoo
Assuming that the velocity profile through the boundary layer is given by a
power-law variation
U= Voo
Calculate the value of n, consistent with the information given above.
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