Boundary Layer Thickness for Turbulent Flow Solution

STEP 0: Pre-Calculation Summary
Formula Used
Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5))
δT = 0.37*x/(ReT^(1/5))
This formula uses 3 Variables
Variables Used
Turbulent Boundary Layer Thickness - (Measured in Meter) - Turbulent 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 Turbulent Flow - Reynolds Number for Turbulent 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 Turbulent Flow: 3500 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
δT = 0.37*x/(ReT^(1/5)) --> 0.37*2.1/(3500^(1/5))
Evaluating ... ...
δT = 0.151917361836111
STEP 3: Convert Result to Output's Unit
0.151917361836111 Meter --> No Conversion Required
FINAL ANSWER
0.151917361836111 0.151917 Meter <-- Turbulent Boundary Layer Thickness
(Calculation completed in 00.020 seconds)

Credits

Created by Shikha Maurya
Indian Institute of Technology (IIT), Bombay
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Amrita School of Engineering (ASE), Vallikavu
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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)
Center of Pressure Location for Cambered Airfoil
Go Center of Pressure = -(Moment Coefficient about Leading Edge*Chord)/Lift Coefficient
Lift Coefficient for Cambered Airfoil
Go Lift Coefficient for Cambered Airfoil = 2*pi*(Angle of Attack-Angle of Zero Lift)
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 Turbulent Flow Formula

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

How to calculate skin friction drag on flat plate?

The boundary layer over a body always starts out as a laminar boundary for some distance from the leading edge, and then transits to a turbulent boundary layer at some point downstream of the leading edge. The skin-friction drag is therefore a combination of laminar skin friction over the forward part of the airfoil, and turbulent skin friction over the remaining part.

How to Calculate Boundary Layer Thickness for Turbulent Flow?

Boundary Layer Thickness for Turbulent Flow calculator uses Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5)) to calculate the Turbulent Boundary Layer Thickness, The Boundary layer thickness for Turbulent flow formula is function of Reynolds number at that location. Turbulent Boundary Layer Thickness is denoted by δT symbol.

How to calculate Boundary Layer Thickness for Turbulent Flow using this online calculator? To use this online calculator for Boundary Layer Thickness for Turbulent Flow, enter Distance on X-Axis (x) & Reynolds Number for Turbulent Flow (ReT) and hit the calculate button. Here is how the Boundary Layer Thickness for Turbulent Flow calculation can be explained with given input values -> 0.151917 = 0.37*2.1/(3500^(1/5)).

FAQ

What is Boundary Layer Thickness for Turbulent Flow?
The Boundary layer thickness for Turbulent flow formula is function of Reynolds number at that location and is represented as δT = 0.37*x/(ReT^(1/5)) or Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5)). Distance on X-Axis is the distance of point measured along x-axis form origin & Reynolds Number for Turbulent 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 Turbulent Flow?
The Boundary layer thickness for Turbulent flow formula is function of Reynolds number at that location is calculated using Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5)). To calculate Boundary Layer Thickness for Turbulent Flow, you need Distance on X-Axis (x) & Reynolds Number for Turbulent Flow (ReT). With our tool, you need to enter the respective value for Distance on X-Axis & Reynolds Number for Turbulent 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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