Boundary Layer Thickness for Laminar Flow Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Flow over Airfoils and Wings

Elementary Flows

Flow and Lift Distribution

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✖Distance on X-Axis is the distance of point measured along x-axis form origin.ⓘ Distance on X-Axis [x]			+10% -10%
✖Reynolds Number for Laminar Flow is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid velocities.ⓘ Reynolds Number for Laminar Flow [Re_L]			+10% -10%

✖Laminar Boundary Layer Thickness is the distance normal to the wall to a point where the flow velocity has essentially reached the 'asymptotic' velocity, or 99 percent of freestream velocity.ⓘ Boundary Layer Thickness for Laminar Flow [δ_L]

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Formula

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Boundary Layer Thickness for Laminar Flow

Formula

`"δ"_{"L"} = 5*"x"/sqrt("Re"_{"L"})`

Example

`"0.247487m"=5*"2.10m"/sqrt("1800")`

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Boundary Layer Thickness for Laminar Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow)
δ_L = 5*x/sqrt(Re_L)
This formula uses 1 Functions, 3 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Laminar Boundary Layer Thickness - (Measured in Meter) - Laminar Boundary Layer Thickness is the distance normal to the wall to a point where the flow velocity has essentially reached the 'asymptotic' velocity, or 99 percent of freestream velocity.
Distance on X-Axis - (Measured in Meter) - Distance on X-Axis is the distance of point measured along x-axis form origin.
Reynolds Number for Laminar Flow - Reynolds Number for Laminar Flow is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid velocities.

STEP 1: Convert Input(s) to Base Unit

Distance on X-Axis: 2.1 Meter --> 2.1 Meter No Conversion Required
Reynolds Number for Laminar Flow: 1800 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

δ_L = 5*x/sqrt(Re_L) --> 5*2.1/sqrt(1800)

Evaluating ... ...

δ_L = 0.247487373415292

STEP 3: Convert Result to Output's Unit

0.247487373415292 Meter --> No Conversion Required

FINAL ANSWER

0.247487373415292 ≈ 0.247487 Meter <-- Laminar Boundary Layer Thickness

(Calculation completed in 00.004 seconds)

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Created by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< 8 Flow over Airfoils Calculators

Boundary Layer Thickness for Laminar Flow

Go Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow)

Lift Coefficient for Cambered Airfoil

Go Lift Coefficient for Cambered Airfoil = 2*pi*((Angle of Attack)-(Angle of Zero Lift))

Center of Pressure Location for Cambered Airfoil

Go Center of Pressure = -(Moment Coefficient about Leading Edge*Chord)/Lift Coefficient

Boundary Layer Thickness for Turbulent Flow

Go Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5))

Skin Friction Drag Coefficient for Flat Plate in Laminar Flow

Go Skin Friction Drag Coefficient = 1.328/(sqrt(Reynolds Number for Laminar Flow))

Skin Friction Drag Coefficient for Flat Plate in Turbulent Flow

Go Skin Friction Drag Coefficient = 0.074/(Reynolds Number for Turbulent Flow^(1/5))

Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory

Go Lift Coefficient = 2*pi*Angle of Attack

Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory

Go Moment Coefficient about Leading Edge = -Lift Coefficient/4

Boundary Layer Thickness for Laminar Flow Formula

Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow)
δ_L = 5*x/sqrt(Re_L)

What is laminar flow?

Laminar flow is the flow in which the streamlines are smooth and regular and a fluid element moves smoothly along a streamline.

Wha is boundary-layer thickness?

The Boundary -ayer thickness is normally defined as the distance from the solid body to the point at which the viscous flow velocity is 99% of the freestream velocity.

How to Calculate Boundary Layer Thickness for Laminar Flow?

Boundary Layer Thickness for Laminar Flow calculator uses Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow) to calculate the Laminar Boundary Layer Thickness, The Boundary Layer Thickness for laminar flow is a measure of the distance from the surface of a solid body, such as an airfoil or a pipe, to the point where the flow velocity reaches approximately 99% of the free stream velocity. Laminar Boundary Layer Thickness is denoted by δ_L symbol.

How to calculate Boundary Layer Thickness for Laminar Flow using this online calculator? To use this online calculator for Boundary Layer Thickness for Laminar Flow, enter Distance on X-Axis (x) & Reynolds Number for Laminar Flow (Re_L) and hit the calculate button. Here is how the Boundary Layer Thickness for Laminar Flow calculation can be explained with given input values -> 0.247487 = 5*2.1/sqrt(1800).

FAQ

What is Boundary Layer Thickness for Laminar Flow?

The Boundary Layer Thickness for laminar flow is a measure of the distance from the surface of a solid body, such as an airfoil or a pipe, to the point where the flow velocity reaches approximately 99% of the free stream velocity and is represented as δ_L = 5*x/sqrt(Re_L) or Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow). Distance on X-Axis is the distance of point measured along x-axis form origin & Reynolds Number for Laminar Flow is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid velocities.

How to calculate Boundary Layer Thickness for Laminar Flow?

The Boundary Layer Thickness for laminar flow is a measure of the distance from the surface of a solid body, such as an airfoil or a pipe, to the point where the flow velocity reaches approximately 99% of the free stream velocity is calculated using Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow). To calculate Boundary Layer Thickness for Laminar Flow, you need Distance on X-Axis (x) & Reynolds Number for Laminar Flow (Re_L). With our tool, you need to enter the respective value for Distance on X-Axis & Reynolds Number for Laminar Flow and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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