Flow-through Pipes & Boundary Layer Theory Study Notes for SSC JE & AE JE Exams

By Sidharth Jain|Updated : June 20th, 2022

Flow-through Pipes & Boundary Layer Theory topic study notes are essential for the preparation of RRB JE, SSC JE, and other AE JE exams. Therefore, a portion of the Fluid Mechanics topic has been covered here to provide aspirants with in-depth knowledge of Flow-through Pipes & Boundary Layer Theory.

Every AE & JE Civil Engineering exam contains questions from Fluid Mechanics. Aspirants face difficulty while tackling or solving questions from the Flow-through Pipes & Boundary Layer Theory topic in SSC JE, RRB JE, or any state AE JE exams. Therefore, aspirants should learn by referring to the Flow-through Pipes & Boundary Layer Theory study notes.

 

Introduction of Losses Through Pipes & Compounding

When fluid flows through pipes, there are losses of energy due to viscous or friction and change in pipe diameter or bends in pipes.

Connections of pipes in series and parallel are termed as compounding of pipes.

Energy losses in pipes are divided into two types based on the amount of losses:

  1. Major Loss.
  2. Minor Loss.

Major Loss

It is calculated by Darcy Weisbach formula

Loss of head due to friction: 

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where:

L = Length of pipe

V = Mean velocity of flow

d = Diameter of pipe

f = friction factor

f'=coefficient of friction

 f= 4f'

 

Chezy’s Formula

In fluid dynamics, Chezy’s formula describes the mean flow velocity of steady, turbulent open channel flow.

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Average velocity V is given by: byjusexamprep

Where: byjusexamprep

i = Head loss per unit length of pipe  (hydraulic slope tanθ)

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Minor Loss

The another type of head loss is minor loss which are induced due to following reasons

Loss due to Sudden Enlargement:

Head loss:14-Head-losses (12)

Loss due to Sudden Contraction:

Head loss: 14-Head-losses (13)

Remember v1 is velocity at point lies in the contracted section.

Loss of Head at Entrance to Pipe:

Head loss: 

14-Head-losses (14)

Loss at Exit from Pipe

Head loss: 14-Head-losses (15)

Combination of Pipes

Pipes may be connected in  parallel, series  or in both. Let see their combinations.

Pipe in Series: In series combination of pipes, the discharge through each pipe will be same.

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In series pipes:

(i). Discharge, Q = A1v1 = A2v2 = A3v3

(ii). The total head loss is the sum of the head losses in each individual pipe.

 

Pipes in Parallel: In parallel combination discharge in main pipe is equal to sum of discharge in each of parallel pipes.

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For Parallel pipes:

(i). Total discharge: Q = Q1 + Q2

(ii). Loss of head in each parallel pipe is same.

i.e. Loss of head in branch pipe 1 = Loss of head in branch pipe 2

 

 

Hydraulic Gradient Line (HGL) and Total Energy Line (TEL)

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HGL → It connects piezometric head  at various points.

TEL → It connects total energy head at various points.

Note:

  1. HGL is always parallel to TEL but lower than TEL by velocity head.
  2. For stationary bodies such as lakes or reservoirs, the HGL and EGL coincide with the free surface of the liquid.
  3. A steep jump or droop occurs in HGL and TEL whenever mechanical energy is added to the fluid (by a pump)or mechanical energy is removed from the fluid (by a turbine) respectively.
  4. byjusexamprep

 

Water Hammer:

When a liquid is flowing through a long pipe fitted with a valve at the end of the pipe and when the valve is closed suddenly a pressure wave of high intensity is generated behind the valve. This pressure wave of high intensity is having the effect of hammering action on the pipe wall. The phenomenon is known as water hammer.

 

Introduction of Boundary layer theory

The boundary layer phenomenon occurs when a fluid flows over a flat plate causing laminar or turbulent flow. This topic defines various parameters such as Energy thickness, Momentum thickness, Boundary layer thickness etc.

  • Ludwig Prandtl developed boundary layer theory in the year 1904.
  • When a real fluid flows over a solid body, fluid velocity at the boundary will be zero. If the boundary is stationary.
  • As we move away from the boundary in the perpendicular direction, velocity increases to the free stream velocity. It means velocity gradient will exist.

Note: velocity gradient 11-Boundary-layer_files (2) does not exist outside the boundary layer as velocity is constant and equal to free stream velocity outside the boundary layer.

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Boundary-Layer Thickness (δ) 

It is the distance from the boundary of the solid body measured in the y-direction to the point where the velocity of the fluid is approximately equal to 0.999 times the free stream velocity (U) of the fluid.

Boundary conditions in boundary layer:

(i) At y = 0, u = 0

(ii) y = δ, u = u

(iii) y = δ, 11-Boundary-layer_files (1)=0

(iv) x = 0, δ = 0

Here, x is the distance in the horizontal direction from the leading edge.

byjusexamprep

Fig.: Boundary layer on a flat plate

Reynolds number (Re11-Boundary-layer_files (3)

For laminar boundary layer (Re)x < 5 × 105 (For flat plate)

For turbulent boundary layer (Re)x > 5 × 105 (For flat plate)

Displacement Thickness (δ*):

It is the distance measured perpendicular from the solid body, by which the boundary should be displaced to compensate for the reduction in flow rate on account of boundary layer formation.

11-Boundary-layer_files (7)

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Momentum Thickness (θ): 

It is the distance measured perpendicular from the solid body, by which the boundary should be displaced to compensate for the reduction in the momentum of the flowing fluid on account of boundary layer formation.

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Energy Thickness (δe): 

It is the distance measured perpendicular from the solid body, by which the boundary should be displaced to compensate for the reduction in kinetic energy of the flowing fluid on account of boundary layer formation.

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Shape Factor(H):

  • The ratio of displacement thickness to momentum thickness is known as the shape factor.
  • Hence: H=δ*/θ
  • This ratio depends simply on the shape of the velocity profile.

 

Von Karman Momentum Integral Equation

11-Boundary-layer_files (15)

where, θ = momentum thickness; ρ = Density of fluid and U = Free stream velocity.

11-Boundary-layer_files (16)

This above equation is applied to:
1. Laminar boundary layers,
2. Transition boundary layers, and
3. Turbulent boundary layer flows.

Local Coefficient of Drag (CD*): 

It is defined as the ratio of the shear stress τ0 to the quantity 11-Boundary-layer_files (17)

It is denoted by 11-Boundary-layer_files (18)

 

Average Coefficient of Drag (CD): 

It is defined as the ratio of the total drag force to the quantity  11-Boundary-layer_files (19)

It is denoted by11-Boundary-layer_files (20)

Where, A = Area of surface, U = Free stream velocity, ρ = Mass density of the fluid.

 

Total drag on a flat plate due to laminar and turbulent boundary layer:

byjusexamprep

Total drag= Laminar drag upto transition boundary + turbulent drag for the whole plate - turbulent drag upto transition boundary

Drag force=FD = ½ ρ × v2 × CD ×A

Blassius Experiment Results:

byjusexamprep
where x = Distance from the leading edge

Rex = Reynold number for length x.

ReL = Reynold number at the end of the plane

For laminar flow, the thickness of the Boundary layer,  δ ∝ √x

                         Shear stress at the solid surface, 11-Boundary-layer_files (28)

Velocity profile for turbulent boundary layer on Flat surface:

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where n =1/7  for Re < 107 but more than 5 × 105                            

Boundary-Layer Separation

The effect of pressure gradient on boundary layer separation can be explained by considering the flow over a curved surface ABCSD, as shown in Fig.


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Along the region CSD of the curved surface, the area of flow increases, and hence the velocity of flow along the direction of fluid decreases. Thus, the pressure increases in the flow direction due to a decrease in velocity. Pressure gradient:  

 

The velocity of the layer adjacent to the solid surface along the length of the solid surface decreases. Thus, the combined effect of positive pressure gradient and surface resistance reduce the momentum.

Location of Separation Point:

The point of separation (S) is obtained from the condition:

11-Boundary-layer_files (30)

For a given velocity profile:

If 11-Boundary-layer_files (32) the flow is separated 

If 11-Boundary-layer_files (34) the flow is on the verge of separation 

If 11-Boundary-layer_files (36) the flow will not separate

Methods of Preventing Separation of Boundary Layer:

  • Supplying additional energy from a blower.
  • Providing a bypass in the slotted
  • Rotating boundary in the direction of flow.
  • Providing small divergence in a diffuser.
  • Providing guide blades in a bend.

Introduction of Drag & Lift

A Stationary fluid exerts a force on a moving body in it. The force is also exerted when the body and fluid move at different velocities, i.e., relative motion between them. 

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Drag (FD):

Drag is the total aerodynamic force (FR) component, which is parallel and in opposition to the body’s motion. 

Lift (FL):

The component of the total force (FR) in the direction perpendicular to the direction of motion is known as ‘lift’. Lift force is considered when the axis of the body is inclined to the direction of fluid flow. If the axis of the body is parallel to the direction of fluid flow, the lift force is zero.

Note.:

The drag and lift will be zero for fluid flow over an ideal and symmetrical body like a sphere or cylinder.

Expression for the Drag and Lift:

Consider an arbitrary shape solid body placed in a real fluid flowing with a uniform velocity U in a horizontal direction as shown in Fig.  Consider a small elemental area dA on the body’s surface.

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The forces acting on the surface area dA are:

  1. Pressure force equal to P × dA acting perpendicular to the surface and
  2. A shear force equal to τ0 × dA acts along the surface's tangential direction.

Let θ = angle made by pressure force with the horizontal direction.

Drag force (FD):  

dFD = (Fpressure + Fshear) in the direction of fluid motion

dFD = pdA cos θ + τodA cos (90° – θ) = pdA cos θ + τ0dA sin θ

∴ Total drag (FD):

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Where:

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The drag and lift for a body moving in a fluid of density ρ, at a uniform velocity (u)

Are calculated mathematically, as:

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 and                           

Where:

CD = Co-efficient of drag

CL = Co-efficient of lift,

A = projected area of the body perpendicular to the direction of flow = Largest

projected area

of the immersed body.

The resultant force is:

 byjusexamprep               

 

The relative contribution of the friction drag and pressure drag in the total drag depends on:

(i). the shape of the immersed body.

(ii). the immersed body position in the fluid, and

(iii). Fluid characteristics.

 

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Flow-through Pipes & Boundary Layer Theory Study Notes FAQs

  • It is mainly important for SSC JE & RRB JE and other state JE exams.

  • It varies from 3 to 4 marks in different AE & JE Exams.

  • Yes, this topic is very much important to understanding Fluid mechanics subject.

  • A compound pipe which consists of several pipes of different lengths and diameters to be replaced by a pipe having a uniform diameter and the same length as that of a compound pipe is called an equivalent pipe.

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